An InterstellarPrecursor Mission
Transcript of An InterstellarPrecursor Mission
JPL PUBLICATION 77-70
An InterstellarPrecursor Mission (NASA-CR-156152) Al fIlERSTELLAR PRECURSOR t178-21173 MISSION (Jet Propulsion Lab) 111 p HC A06UF A01 CSCL 22A
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JPL PUBLICATION 77-70
An Interstellar Precursor Mission
L D J affe C Ivie J-- Lewis R Lipes H N Norton J W Stearns L D Stimpson P Weissman
October 30 1977
National Aeronautics and Space Administration
Jet Propulsion Laboratory California Institute of Technology Pasadena California
Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration
77-70
PREFACE-
The work described in this report was performed by the Earthand Space
Sciences Systems Telecommunications Science and Engineering Control and
Energy Conversion Applied Mechanics and Information Systems Divisions of
the Jet Propulsion Laboratory for NASA Ames Research Center under NASA
OAST Program 790 Space Systems Studies Stanley R Sadin sponsor
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ABSTRACT
A mntsion out of the planetary system with launch about the year 2000
could provide valuable scientific data as well as test some of the technology
for a later mission to another star A mission to a star is not expected to
be practical around 2000 because the flight time with the technology then
available is expected to exceed 10000 yr
Primary scientific objectives for the precursor mission concern
characteristics of the heliopause the interstellar medium stellar distances
(by parallax measurements) low energy cosmic rays interplanetary gas distrishy
bution and mass of the solar system Secondary objectives include investigashy
tion of Pluto Candidate science instruments are suggested
The mission should extend to 500-1000 AU from the sun A heliocentric
hyperbolic escape velocity of 50-100 kms or more is needed to attain this
distance within a reasonable mission duration The trajectory should be
toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy
ter can be included A second mission targeted parallel to the solar axis
would also be worthwhile
The mission duration is 20 years with an extended mission to a total
of 50 years A system using 1 or 2 stages of nuclear electric propulsion was
selected as a possible baseline The most promising alternatives are ultralight
solar sails or laser sailing with the lasers in Earth orbit for example
The NEP baseline design allows the option of carrying a Pluto orbiter as a
daughter spacecraft
Within the limited depth of this study individual spacecraft systems
for the mission are considered technology requirements and problem areas
noted and a number of recommendations made for technology study and advanced
development The most critical technology needs include attainment of 50-yr
spacecraft lifetime and development of a long-life NEP system
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RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT
FOR EXTRAPLANETARY MISSION
To permit an extraplanetary mission such as that described in this
reportto commence about the year 2000 efforts are recommended on the
following topics In general a study should be initiated first followed
by development effort as indicated by the study
First priority
Starting work on the following topics is considered of first priority
in view of their importance to the mission and the time required for the
advance development
1) Design and fabrication techniques that will provide 50-year spaceshy
craft lifetime
2) Nuclear electric propulsion with operating times of 10 years or more at
full power and able to operate at low power levels for attitude control and
spacecraft power to a total of 50 years
3) Ultralight solar sails including their impact upon spacecraft and
mission design
4) Laser sailing systems including their impact upon spacecraft and
mission design
5) Detailing and application of spacecraft quality assurance and relishy
ability methods utilizing test times much shorter than the intended lifetime
Second priority
Other topics that will require advance effort beyond that likely without
special attention include
6) Spacecraft bearings and moving parts with 50-yr lifetime 2
Neutral gas mass spectrometer for measuring concentrations of 10shy
7)
0-10- atomcm3 with 50-yr lifetime
8) Techniques to predict long-time behavior of spacecraft materials from
short-time tests
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9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
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TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
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TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
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TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
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INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
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This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
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SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
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90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
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considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
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measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
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and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
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and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
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Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
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A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
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around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
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A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
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300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
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TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
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If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
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MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
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MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
44
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
45
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
46
77-70
assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
47
77-70
system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
48
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
49
77-70
on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
50
77-70
70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
51
77-70
Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
52
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
53
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
54
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
77-70
RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
59
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
61
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
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77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
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own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
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APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335
2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414
50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335
Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A
4478828 50P4377 5gqQ2p5 9P5471
SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980
90017P 500364 509(05650O340 500342 50033-5i
P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846
50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP
(06A6 PS4nu4A rnn668 p6qnnl
fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144
nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710
5(0it4p 360o207 7 8A 7 05 9
r00465 3811414 5lf45 1IA0S075 nn441 U0234
i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln
srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0
g0nn03 snonI
q
fnniAg onnu53
qnnil6 0n0itl
5fnlnrlq 5n014nq tfl030 q
5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839
5100 5200
5403251 5508794
500328 500322
5401959 5507502
9003P8 900322
540I015 S001PR R506r5P 900322
53qq0 5504933
qn0i9g nn0pn
K9q7469 530O
50nnxpQ 900322
59464q 550n187
3n9 5nn39
5300 5400
5614336 5719877
500316 900310
5613044 5718589
500316 500310
5612100 5717641
r00316 500310
r610479 5716016
g50n16 nn2n
W0R549 r714n85
5n0316 qnOxAl1
q6n07l4 5711PAn
5nn116 Fnn 11
5500 5600 5700 5800 5)00 6000
5829416 5930955 6036492 614P028 6247563 6353098
rn0304 50029 5002q4 50028q 500284 500279
5824124 5920663 6035200 6140736 6246271 6351805
90035 5n0p9 090q4 500289 5n024 500270
rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861
500305 g0olqQo RnOq4 500280 50OP4 90027Q
21555 0pflo S826in 6138166 649701 614q239
500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP
50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q
R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4
5nnxnK srn Q gn09Q4 500n0q nnf04
gnnon
PRW flr 03W77 nArr 7
V-INFINITY = 600 KMS
T - YRS 0=
RAn 1AU
VEL q =
RAr) 3 AU
VEL n =
PAn 5 AU
Vft n = 10
PA) Atl
VFL a = PAn
20 MI VEL PAMn
5p fU VVl
00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60
56979 83199
6P5413 617524
55061 8110l
695863 617714 A1477
A61246324q76 A17P00 807 o 0
APA17 AInO
F56o A14l1
6pov7q 617AAe
7r Qt11171
61nnpQ 615RA7
80 100
10910( 134926
61340l 610860
10A043 133R4q
613R2 610047
lo7177 1st3e1
61361 11flnn
tOAgqo 1502c
A1Po n67or 611AI3940611non
e137n i155 13 flW s
AlAq0 AinIft
120 140
160656 186325
609134 607884
15057P 185236
60q2n5607Q30
1S8872 jAlrp7
600opg07aA0
157O014 IPI1r7
6flQO 008113
J-1N IRinfn
n031 6n0S6
Ierl 14Ut
6mnn An7017
160 180
211940 237538
606q36 6n6103
210895 236441
6n6072 6n6p2
Pjn130 PA5710
6n60q5 6n6940
rnnoo P34654
A7nn O9Apt
20A467 p 43Q30
A7nq1 606P7
11fn PAn I
AnSnSn AnAfl
200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240
28A637 314157
605101 604688
28753f 31305
6n510 6047n5
P6n05 619131 1193I6fl4
2897n0 i 6
65103 An311206
p4tr5 n-ins
6n9168 An4746
5nptSn A
-tpo Anq1 n AA0471
260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340
365150 3Q0628 416096 441554
6n4036 603773 6n3543 603330
364044 389521 41407 440445
6n4048 603784 603592 613348
363031 388780 41P4t5
UIQ0f
6n4nti f 61370 6n3590
An315A
3876A7 414j31n 43q41U
A1u1AOtq Aen 60n60 A1A62
IAJ61o R866P4
u1pnrq u37T 4 a
6n4n8 6fl1I 6ndeg9 A370
16un 3A611 41I-Afln
41in1
AnflnAA Anfnlp sMIn 71 6n3A
360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa
380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480
568742 594162 619579
602594 6024A3 602382
56762P 5P3o5 618466
6n29q 6n2408 6n2386
566p8f 9inf deg17719
6112603 6fn2qj6n2980
966qq 5011j9616P7
Anp6np 6P406 AnPQI
R645n 58o53 e135i
An2613
69Rn9109
R65hn qnoA=IA
6fn9613 Annl 6m Q
o 500 520
644991 67039q
602P88 61 22Nt
643R77 66q0R2
e0P2QP 6n22n9
641126 66A533
A6p295 6129oA
641035 6673140
A62paq AnP1
64degnr 666145
612311 6npois
Aqnq4n 6egna
An1 An1 7
-J 0
540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n
721206 746605
60207 601)77
720092 749412
602050 6O10O
71031R 744736
6npn0p 601ORP
71140 743S35
60n15 Anlpq
7164P7 74P31
A9nq 69t1A0
716455 74 17I
6nn6n 6nlno
600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640
707394 822784
601851 601704
79627A 82166q
601A54 6n17q7
705p4 n2024
61n186 611708
7q4 p07fl7
n 6I0t85q Anln01
70368 lP46
601n61 A1n14
7qP4k7 ct77
6118nl 60inn
660 680
84173 873559
601741 6016q0
847057 872441
6n1743 6n1692
A4Ao AviAv
6n1745 6016qu
A49n 870477
Af1747 An1A06
A4314U pAQP99
snstyn 601AO
A4lll 86R451
An19i 6 17n0
700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760
949706 975004
601559 601514
948580 97096A
60197 601516
9u7983 Q73plO
601558 AnlIr17
046618 071)09
6n11560 An 191 a
45147 07071n
6nlq6 611spl
040MA4A6158 Q68nn finICD3
7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840
1051210 1076583
601405 601372
1050091 1075466
6n1406 6n1373
ln4335 1074707
6nln7 0n1374
1048116 1073487
n14nq tnuARPn An1W76 107105
An1411 611177
10481c7 I071157
Af1012 Aflt1A
860 880
1101954 1127324
601340 601310
1100837 1126206
601342 601311
130007A 11Pq447
601141 6131P
10857 1124PP5
6n1144 6n1314
loq7961ll22q2A
601146 6n1 tq
IQA4A 1121838
An14 eniI7
900 920
1152692 1178060
6012R1 601254
1151579 117694P
6012R3 601255
1150A81 1176183
60128p3 6n1256
1j4q 3 11749qq
6nIP9 60157
11P n 1173653
6IPA6 60158
1147176 117P9916
An1 4 6019 0
940 960
1203426 1228791
601227 601202
1202308 1227673
601228 601203
12019q 12P6013
601P20 60lpo4
12003P4 122i60
601231 An6p125
xo001 12p4376
601039 6n1006
11QT899 1P21t5
6n1943 61nl9
980 1254155 601178 1253037 601179 1252277 6001180 1251051 A0f11 1 1240736 6011R2 1240519 601183 1000 1279518 601154 1278400 601155 1277640 01156 1276413 601157 1p70q6 6011RA 127181 An1O
PRW DATF 011077 PArr Is
V-TNFINITY =600 KMS
S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL
1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql
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r PUBLICATION 77-70
NOTICE
THIS DOCUMENT HAS BEEN REPRODUCED
FROM THE BEST COPY FURNISHED US BY
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IS RECOGNIZED THAT CERTAIN PORTIONS
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JPL PUBLICATION 77-70
An Interstellar Precursor Mission
L D J affe C Ivie J-- Lewis R Lipes H N Norton J W Stearns L D Stimpson P Weissman
October 30 1977
National Aeronautics and Space Administration
Jet Propulsion Laboratory California Institute of Technology Pasadena California
Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration
77-70
PREFACE-
The work described in this report was performed by the Earthand Space
Sciences Systems Telecommunications Science and Engineering Control and
Energy Conversion Applied Mechanics and Information Systems Divisions of
the Jet Propulsion Laboratory for NASA Ames Research Center under NASA
OAST Program 790 Space Systems Studies Stanley R Sadin sponsor
iii
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ABSTRACT
A mntsion out of the planetary system with launch about the year 2000
could provide valuable scientific data as well as test some of the technology
for a later mission to another star A mission to a star is not expected to
be practical around 2000 because the flight time with the technology then
available is expected to exceed 10000 yr
Primary scientific objectives for the precursor mission concern
characteristics of the heliopause the interstellar medium stellar distances
(by parallax measurements) low energy cosmic rays interplanetary gas distrishy
bution and mass of the solar system Secondary objectives include investigashy
tion of Pluto Candidate science instruments are suggested
The mission should extend to 500-1000 AU from the sun A heliocentric
hyperbolic escape velocity of 50-100 kms or more is needed to attain this
distance within a reasonable mission duration The trajectory should be
toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy
ter can be included A second mission targeted parallel to the solar axis
would also be worthwhile
The mission duration is 20 years with an extended mission to a total
of 50 years A system using 1 or 2 stages of nuclear electric propulsion was
selected as a possible baseline The most promising alternatives are ultralight
solar sails or laser sailing with the lasers in Earth orbit for example
The NEP baseline design allows the option of carrying a Pluto orbiter as a
daughter spacecraft
Within the limited depth of this study individual spacecraft systems
for the mission are considered technology requirements and problem areas
noted and a number of recommendations made for technology study and advanced
development The most critical technology needs include attainment of 50-yr
spacecraft lifetime and development of a long-life NEP system
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RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT
FOR EXTRAPLANETARY MISSION
To permit an extraplanetary mission such as that described in this
reportto commence about the year 2000 efforts are recommended on the
following topics In general a study should be initiated first followed
by development effort as indicated by the study
First priority
Starting work on the following topics is considered of first priority
in view of their importance to the mission and the time required for the
advance development
1) Design and fabrication techniques that will provide 50-year spaceshy
craft lifetime
2) Nuclear electric propulsion with operating times of 10 years or more at
full power and able to operate at low power levels for attitude control and
spacecraft power to a total of 50 years
3) Ultralight solar sails including their impact upon spacecraft and
mission design
4) Laser sailing systems including their impact upon spacecraft and
mission design
5) Detailing and application of spacecraft quality assurance and relishy
ability methods utilizing test times much shorter than the intended lifetime
Second priority
Other topics that will require advance effort beyond that likely without
special attention include
6) Spacecraft bearings and moving parts with 50-yr lifetime 2
Neutral gas mass spectrometer for measuring concentrations of 10shy
7)
0-10- atomcm3 with 50-yr lifetime
8) Techniques to predict long-time behavior of spacecraft materials from
short-time tests
v
77-7o
9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
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TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
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Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
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Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
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INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
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This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
77-70
SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
77-70
considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
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measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
10
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and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
11
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and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
12
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
13
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
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Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
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A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
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around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
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A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
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300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
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TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
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If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
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MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
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MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
44
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
45
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
46
77-70
assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
47
77-70
system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
48
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
49
77-70
on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
50
77-70
70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
51
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
52
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
53
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
54
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
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RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
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77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
79
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
80
77-70
This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
81
77-70
own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
82
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APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335
2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414
50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335
Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A
4478828 50P4377 5gqQ2p5 9P5471
SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980
90017P 500364 509(05650O340 500342 50033-5i
P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846
50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP
(06A6 PS4nu4A rnn668 p6qnnl
fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144
nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710
5(0it4p 360o207 7 8A 7 05 9
r00465 3811414 5lf45 1IA0S075 nn441 U0234
i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln
srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0
g0nn03 snonI
q
fnniAg onnu53
qnnil6 0n0itl
5fnlnrlq 5n014nq tfl030 q
5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839
5100 5200
5403251 5508794
500328 500322
5401959 5507502
9003P8 900322
540I015 S001PR R506r5P 900322
53qq0 5504933
qn0i9g nn0pn
K9q7469 530O
50nnxpQ 900322
59464q 550n187
3n9 5nn39
5300 5400
5614336 5719877
500316 900310
5613044 5718589
500316 500310
5612100 5717641
r00316 500310
r610479 5716016
g50n16 nn2n
W0R549 r714n85
5n0316 qnOxAl1
q6n07l4 5711PAn
5nn116 Fnn 11
5500 5600 5700 5800 5)00 6000
5829416 5930955 6036492 614P028 6247563 6353098
rn0304 50029 5002q4 50028q 500284 500279
5824124 5920663 6035200 6140736 6246271 6351805
90035 5n0p9 090q4 500289 5n024 500270
rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861
500305 g0olqQo RnOq4 500280 50OP4 90027Q
21555 0pflo S826in 6138166 649701 614q239
500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP
50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q
R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4
5nnxnK srn Q gn09Q4 500n0q nnf04
gnnon
PRW flr 03W77 nArr 7
V-INFINITY = 600 KMS
T - YRS 0=
RAn 1AU
VEL q =
RAr) 3 AU
VEL n =
PAn 5 AU
Vft n = 10
PA) Atl
VFL a = PAn
20 MI VEL PAMn
5p fU VVl
00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60
56979 83199
6P5413 617524
55061 8110l
695863 617714 A1477
A61246324q76 A17P00 807 o 0
APA17 AInO
F56o A14l1
6pov7q 617AAe
7r Qt11171
61nnpQ 615RA7
80 100
10910( 134926
61340l 610860
10A043 133R4q
613R2 610047
lo7177 1st3e1
61361 11flnn
tOAgqo 1502c
A1Po n67or 611AI3940611non
e137n i155 13 flW s
AlAq0 AinIft
120 140
160656 186325
609134 607884
15057P 185236
60q2n5607Q30
1S8872 jAlrp7
600opg07aA0
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r PUBLICATION 77-70
JPL PUBLICATION 77-70
An Interstellar Precursor Mission
L D J affe C Ivie J-- Lewis R Lipes H N Norton J W Stearns L D Stimpson P Weissman
October 30 1977
National Aeronautics and Space Administration
Jet Propulsion Laboratory California Institute of Technology Pasadena California
Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration
77-70
PREFACE-
The work described in this report was performed by the Earthand Space
Sciences Systems Telecommunications Science and Engineering Control and
Energy Conversion Applied Mechanics and Information Systems Divisions of
the Jet Propulsion Laboratory for NASA Ames Research Center under NASA
OAST Program 790 Space Systems Studies Stanley R Sadin sponsor
iii
77-70
ABSTRACT
A mntsion out of the planetary system with launch about the year 2000
could provide valuable scientific data as well as test some of the technology
for a later mission to another star A mission to a star is not expected to
be practical around 2000 because the flight time with the technology then
available is expected to exceed 10000 yr
Primary scientific objectives for the precursor mission concern
characteristics of the heliopause the interstellar medium stellar distances
(by parallax measurements) low energy cosmic rays interplanetary gas distrishy
bution and mass of the solar system Secondary objectives include investigashy
tion of Pluto Candidate science instruments are suggested
The mission should extend to 500-1000 AU from the sun A heliocentric
hyperbolic escape velocity of 50-100 kms or more is needed to attain this
distance within a reasonable mission duration The trajectory should be
toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy
ter can be included A second mission targeted parallel to the solar axis
would also be worthwhile
The mission duration is 20 years with an extended mission to a total
of 50 years A system using 1 or 2 stages of nuclear electric propulsion was
selected as a possible baseline The most promising alternatives are ultralight
solar sails or laser sailing with the lasers in Earth orbit for example
The NEP baseline design allows the option of carrying a Pluto orbiter as a
daughter spacecraft
Within the limited depth of this study individual spacecraft systems
for the mission are considered technology requirements and problem areas
noted and a number of recommendations made for technology study and advanced
development The most critical technology needs include attainment of 50-yr
spacecraft lifetime and development of a long-life NEP system
iv
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RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT
FOR EXTRAPLANETARY MISSION
To permit an extraplanetary mission such as that described in this
reportto commence about the year 2000 efforts are recommended on the
following topics In general a study should be initiated first followed
by development effort as indicated by the study
First priority
Starting work on the following topics is considered of first priority
in view of their importance to the mission and the time required for the
advance development
1) Design and fabrication techniques that will provide 50-year spaceshy
craft lifetime
2) Nuclear electric propulsion with operating times of 10 years or more at
full power and able to operate at low power levels for attitude control and
spacecraft power to a total of 50 years
3) Ultralight solar sails including their impact upon spacecraft and
mission design
4) Laser sailing systems including their impact upon spacecraft and
mission design
5) Detailing and application of spacecraft quality assurance and relishy
ability methods utilizing test times much shorter than the intended lifetime
Second priority
Other topics that will require advance effort beyond that likely without
special attention include
6) Spacecraft bearings and moving parts with 50-yr lifetime 2
Neutral gas mass spectrometer for measuring concentrations of 10shy
7)
0-10- atomcm3 with 50-yr lifetime
8) Techniques to predict long-time behavior of spacecraft materials from
short-time tests
v
77-7o
9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
vi
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TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
vii
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Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
viii
77-70
Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
ix
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
x
77-70
INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
1
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
2
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
77-70
This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
77-70
SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
5
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
77-70
considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
9
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measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
10
77-70
and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
11
77-70
and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
12
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
13
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
77-70
Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
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A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
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around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
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A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
77-70
300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
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TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
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If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
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MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
77-70
MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
44
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
46
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assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
47
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system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
49
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on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
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70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
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RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
67
77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
81
77-70
own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
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APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335
2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414
50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335
Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A
4478828 50P4377 5gqQ2p5 9P5471
SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980
90017P 500364 509(05650O340 500342 50033-5i
P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846
50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP
(06A6 PS4nu4A rnn668 p6qnnl
fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144
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r PUBLICATION 77-70
Prepared Under Contract No NAS 7-100 National Aeronautics and Space Administration
77-70
PREFACE-
The work described in this report was performed by the Earthand Space
Sciences Systems Telecommunications Science and Engineering Control and
Energy Conversion Applied Mechanics and Information Systems Divisions of
the Jet Propulsion Laboratory for NASA Ames Research Center under NASA
OAST Program 790 Space Systems Studies Stanley R Sadin sponsor
iii
77-70
ABSTRACT
A mntsion out of the planetary system with launch about the year 2000
could provide valuable scientific data as well as test some of the technology
for a later mission to another star A mission to a star is not expected to
be practical around 2000 because the flight time with the technology then
available is expected to exceed 10000 yr
Primary scientific objectives for the precursor mission concern
characteristics of the heliopause the interstellar medium stellar distances
(by parallax measurements) low energy cosmic rays interplanetary gas distrishy
bution and mass of the solar system Secondary objectives include investigashy
tion of Pluto Candidate science instruments are suggested
The mission should extend to 500-1000 AU from the sun A heliocentric
hyperbolic escape velocity of 50-100 kms or more is needed to attain this
distance within a reasonable mission duration The trajectory should be
toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy
ter can be included A second mission targeted parallel to the solar axis
would also be worthwhile
The mission duration is 20 years with an extended mission to a total
of 50 years A system using 1 or 2 stages of nuclear electric propulsion was
selected as a possible baseline The most promising alternatives are ultralight
solar sails or laser sailing with the lasers in Earth orbit for example
The NEP baseline design allows the option of carrying a Pluto orbiter as a
daughter spacecraft
Within the limited depth of this study individual spacecraft systems
for the mission are considered technology requirements and problem areas
noted and a number of recommendations made for technology study and advanced
development The most critical technology needs include attainment of 50-yr
spacecraft lifetime and development of a long-life NEP system
iv
77-70
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT
FOR EXTRAPLANETARY MISSION
To permit an extraplanetary mission such as that described in this
reportto commence about the year 2000 efforts are recommended on the
following topics In general a study should be initiated first followed
by development effort as indicated by the study
First priority
Starting work on the following topics is considered of first priority
in view of their importance to the mission and the time required for the
advance development
1) Design and fabrication techniques that will provide 50-year spaceshy
craft lifetime
2) Nuclear electric propulsion with operating times of 10 years or more at
full power and able to operate at low power levels for attitude control and
spacecraft power to a total of 50 years
3) Ultralight solar sails including their impact upon spacecraft and
mission design
4) Laser sailing systems including their impact upon spacecraft and
mission design
5) Detailing and application of spacecraft quality assurance and relishy
ability methods utilizing test times much shorter than the intended lifetime
Second priority
Other topics that will require advance effort beyond that likely without
special attention include
6) Spacecraft bearings and moving parts with 50-yr lifetime 2
Neutral gas mass spectrometer for measuring concentrations of 10shy
7)
0-10- atomcm3 with 50-yr lifetime
8) Techniques to predict long-time behavior of spacecraft materials from
short-time tests
v
77-7o
9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
vi
77-70
TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
vii
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Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
viii
77-70
Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
ix
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
x
77-70
INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
1
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
2
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
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This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
77-70
SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
5
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
77-70
considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
9
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measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
10
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and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
11
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and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
12
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
13
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
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Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
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A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
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around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
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A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
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300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
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TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
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If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
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MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
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MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
44
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
46
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assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
47
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system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
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on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
50
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70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
51
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
77-70
RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
67
77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
81
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own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
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APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
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r PUBLICATION 77-70
77-70
PREFACE-
The work described in this report was performed by the Earthand Space
Sciences Systems Telecommunications Science and Engineering Control and
Energy Conversion Applied Mechanics and Information Systems Divisions of
the Jet Propulsion Laboratory for NASA Ames Research Center under NASA
OAST Program 790 Space Systems Studies Stanley R Sadin sponsor
iii
77-70
ABSTRACT
A mntsion out of the planetary system with launch about the year 2000
could provide valuable scientific data as well as test some of the technology
for a later mission to another star A mission to a star is not expected to
be practical around 2000 because the flight time with the technology then
available is expected to exceed 10000 yr
Primary scientific objectives for the precursor mission concern
characteristics of the heliopause the interstellar medium stellar distances
(by parallax measurements) low energy cosmic rays interplanetary gas distrishy
bution and mass of the solar system Secondary objectives include investigashy
tion of Pluto Candidate science instruments are suggested
The mission should extend to 500-1000 AU from the sun A heliocentric
hyperbolic escape velocity of 50-100 kms or more is needed to attain this
distance within a reasonable mission duration The trajectory should be
toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy
ter can be included A second mission targeted parallel to the solar axis
would also be worthwhile
The mission duration is 20 years with an extended mission to a total
of 50 years A system using 1 or 2 stages of nuclear electric propulsion was
selected as a possible baseline The most promising alternatives are ultralight
solar sails or laser sailing with the lasers in Earth orbit for example
The NEP baseline design allows the option of carrying a Pluto orbiter as a
daughter spacecraft
Within the limited depth of this study individual spacecraft systems
for the mission are considered technology requirements and problem areas
noted and a number of recommendations made for technology study and advanced
development The most critical technology needs include attainment of 50-yr
spacecraft lifetime and development of a long-life NEP system
iv
77-70
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT
FOR EXTRAPLANETARY MISSION
To permit an extraplanetary mission such as that described in this
reportto commence about the year 2000 efforts are recommended on the
following topics In general a study should be initiated first followed
by development effort as indicated by the study
First priority
Starting work on the following topics is considered of first priority
in view of their importance to the mission and the time required for the
advance development
1) Design and fabrication techniques that will provide 50-year spaceshy
craft lifetime
2) Nuclear electric propulsion with operating times of 10 years or more at
full power and able to operate at low power levels for attitude control and
spacecraft power to a total of 50 years
3) Ultralight solar sails including their impact upon spacecraft and
mission design
4) Laser sailing systems including their impact upon spacecraft and
mission design
5) Detailing and application of spacecraft quality assurance and relishy
ability methods utilizing test times much shorter than the intended lifetime
Second priority
Other topics that will require advance effort beyond that likely without
special attention include
6) Spacecraft bearings and moving parts with 50-yr lifetime 2
Neutral gas mass spectrometer for measuring concentrations of 10shy
7)
0-10- atomcm3 with 50-yr lifetime
8) Techniques to predict long-time behavior of spacecraft materials from
short-time tests
v
77-7o
9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
vi
77-70
TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
vii
77-70
Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
viii
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Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
ix
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
x
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INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
1
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
2
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
77-70
This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
77-70
SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
5
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
77-70
considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
9
77-70
measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
10
77-70
and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
11
77-70
and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
12
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
13
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
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Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
77-70
A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
77-70
around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
77-70
A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
77-70
300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
77-70
TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
77-70
If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
77-70
MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
77-70
MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
44
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
45
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
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assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
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system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
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on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
50
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70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
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RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
67
77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
69
77-70
orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
70
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
71
77-70
REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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77-70
A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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77-70
A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
74
77-70
APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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77-70
APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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77-70
APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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77-70
CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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77-70
This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
81
77-70
own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
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77-70
APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
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r PUBLICATION 77-70
77-70
ABSTRACT
A mntsion out of the planetary system with launch about the year 2000
could provide valuable scientific data as well as test some of the technology
for a later mission to another star A mission to a star is not expected to
be practical around 2000 because the flight time with the technology then
available is expected to exceed 10000 yr
Primary scientific objectives for the precursor mission concern
characteristics of the heliopause the interstellar medium stellar distances
(by parallax measurements) low energy cosmic rays interplanetary gas distrishy
bution and mass of the solar system Secondary objectives include investigashy
tion of Pluto Candidate science instruments are suggested
The mission should extend to 500-1000 AU from the sun A heliocentric
hyperbolic escape velocity of 50-100 kms or more is needed to attain this
distance within a reasonable mission duration The trajectory should be
toward the incoming interstellar wind For a year 2000 launch a Pluto encounshy
ter can be included A second mission targeted parallel to the solar axis
would also be worthwhile
The mission duration is 20 years with an extended mission to a total
of 50 years A system using 1 or 2 stages of nuclear electric propulsion was
selected as a possible baseline The most promising alternatives are ultralight
solar sails or laser sailing with the lasers in Earth orbit for example
The NEP baseline design allows the option of carrying a Pluto orbiter as a
daughter spacecraft
Within the limited depth of this study individual spacecraft systems
for the mission are considered technology requirements and problem areas
noted and a number of recommendations made for technology study and advanced
development The most critical technology needs include attainment of 50-yr
spacecraft lifetime and development of a long-life NEP system
iv
77-70
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT
FOR EXTRAPLANETARY MISSION
To permit an extraplanetary mission such as that described in this
reportto commence about the year 2000 efforts are recommended on the
following topics In general a study should be initiated first followed
by development effort as indicated by the study
First priority
Starting work on the following topics is considered of first priority
in view of their importance to the mission and the time required for the
advance development
1) Design and fabrication techniques that will provide 50-year spaceshy
craft lifetime
2) Nuclear electric propulsion with operating times of 10 years or more at
full power and able to operate at low power levels for attitude control and
spacecraft power to a total of 50 years
3) Ultralight solar sails including their impact upon spacecraft and
mission design
4) Laser sailing systems including their impact upon spacecraft and
mission design
5) Detailing and application of spacecraft quality assurance and relishy
ability methods utilizing test times much shorter than the intended lifetime
Second priority
Other topics that will require advance effort beyond that likely without
special attention include
6) Spacecraft bearings and moving parts with 50-yr lifetime 2
Neutral gas mass spectrometer for measuring concentrations of 10shy
7)
0-10- atomcm3 with 50-yr lifetime
8) Techniques to predict long-time behavior of spacecraft materials from
short-time tests
v
77-7o
9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
vi
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TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
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Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
viii
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Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
ix
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
x
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INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
1
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
2
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
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This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
77-70
SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
5
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
77-70
considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
9
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measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
10
77-70
and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
11
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and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
12
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
13
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
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Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
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A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
77-70
around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
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A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
77-70
300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
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TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
77-70
If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
77-70
hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
77-70
MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
77-70
MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
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assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
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system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
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on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
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70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
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RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
67
77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
71
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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77-70
A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
81
77-70
own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
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APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335
2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414
50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335
Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A
4478828 50P4377 5gqQ2p5 9P5471
SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980
90017P 500364 509(05650O340 500342 50033-5i
P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846
50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP
(06A6 PS4nu4A rnn668 p6qnnl
fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144
nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710
5(0it4p 360o207 7 8A 7 05 9
r00465 3811414 5lf45 1IA0S075 nn441 U0234
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5100 5200
5403251 5508794
500328 500322
5401959 5507502
9003P8 900322
540I015 S001PR R506r5P 900322
53qq0 5504933
qn0i9g nn0pn
K9q7469 530O
50nnxpQ 900322
59464q 550n187
3n9 5nn39
5300 5400
5614336 5719877
500316 900310
5613044 5718589
500316 500310
5612100 5717641
r00316 500310
r610479 5716016
g50n16 nn2n
W0R549 r714n85
5n0316 qnOxAl1
q6n07l4 5711PAn
5nn116 Fnn 11
5500 5600 5700 5800 5)00 6000
5829416 5930955 6036492 614P028 6247563 6353098
rn0304 50029 5002q4 50028q 500284 500279
5824124 5920663 6035200 6140736 6246271 6351805
90035 5n0p9 090q4 500289 5n024 500270
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500305 g0olqQo RnOq4 500280 50OP4 90027Q
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V-INFINITY = 600 KMS
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200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240
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7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840
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1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql
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S 5200 6599481 600224 6998358 6n02P4 6rQ7591l 60024 69q6339 6nnPP4 Ati40na 6noP04 fi9Q9011 Ann4 530 707 606724979 6n0P20 6724P08 60npp0 672PQ91 6nnP 0 67Plr 6n0nln0 671n l~ Aftdegni9 5400 6852713 600216 68q159n 6n02t6 6A9n824 60016 694q567 A00P16 6A4914n 6nn0gt16 6n4At Ann 16 5500 6979327 60023P 697820r 6n02t2 607743A 600pip 6Q76181 6nnP12 -6q7475i4 6n0OgtIP 607p74A 6nplp
2 5600 7105941 600208 7104819 6n0208 71g409P 6no n8 71nP709 AnfnPnA 71n136A 6nnpnR 7nQ0j9A 6ftnoAR 4 - 5700 7232555 6n0204 723143P 6n0n4 7P3066t 6n0p04 7p2 QnA 60npn4 7PP7Q n 60flp05 7r 6Anln
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S 6000 7612390 6n0194 7611267 600104 76|A900 6n0194 760OP43 A0njQ4 76n7814 fi0n1o4 76n971) Annin4
r PUBLICATION 77-70
77-70
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT
FOR EXTRAPLANETARY MISSION
To permit an extraplanetary mission such as that described in this
reportto commence about the year 2000 efforts are recommended on the
following topics In general a study should be initiated first followed
by development effort as indicated by the study
First priority
Starting work on the following topics is considered of first priority
in view of their importance to the mission and the time required for the
advance development
1) Design and fabrication techniques that will provide 50-year spaceshy
craft lifetime
2) Nuclear electric propulsion with operating times of 10 years or more at
full power and able to operate at low power levels for attitude control and
spacecraft power to a total of 50 years
3) Ultralight solar sails including their impact upon spacecraft and
mission design
4) Laser sailing systems including their impact upon spacecraft and
mission design
5) Detailing and application of spacecraft quality assurance and relishy
ability methods utilizing test times much shorter than the intended lifetime
Second priority
Other topics that will require advance effort beyond that likely without
special attention include
6) Spacecraft bearings and moving parts with 50-yr lifetime 2
Neutral gas mass spectrometer for measuring concentrations of 10shy
7)
0-10- atomcm3 with 50-yr lifetime
8) Techniques to predict long-time behavior of spacecraft materials from
short-time tests
v
77-7o
9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
vi
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TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
vii
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Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
viii
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Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
ix
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
x
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INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
1
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
2
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
77-70
This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
77-70
SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
5
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
77-70
considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
77-70
by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
9
77-70
measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
10
77-70
and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
11
77-70
and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
12
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
13
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
77-70
Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
77-70
A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
77-70
around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
77-70
A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
77-70
300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
77-70
TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
77-70
If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
77-70
MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
77-70
MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
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assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
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system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
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on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
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70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
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RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
67
77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
81
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own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
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APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335
2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414
50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335
Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A
4478828 50P4377 5gqQ2p5 9P5471
SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980
90017P 500364 509(05650O340 500342 50033-5i
P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846
50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP
(06A6 PS4nu4A rnn668 p6qnnl
fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144
nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710
5(0it4p 360o207 7 8A 7 05 9
r00465 3811414 5lf45 1IA0S075 nn441 U0234
i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln
srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0
g0nn03 snonI
q
fnniAg onnu53
qnnil6 0n0itl
5fnlnrlq 5n014nq tfl030 q
5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839
5100 5200
5403251 5508794
500328 500322
5401959 5507502
9003P8 900322
540I015 S001PR R506r5P 900322
53qq0 5504933
qn0i9g nn0pn
K9q7469 530O
50nnxpQ 900322
59464q 550n187
3n9 5nn39
5300 5400
5614336 5719877
500316 900310
5613044 5718589
500316 500310
5612100 5717641
r00316 500310
r610479 5716016
g50n16 nn2n
W0R549 r714n85
5n0316 qnOxAl1
q6n07l4 5711PAn
5nn116 Fnn 11
5500 5600 5700 5800 5)00 6000
5829416 5930955 6036492 614P028 6247563 6353098
rn0304 50029 5002q4 50028q 500284 500279
5824124 5920663 6035200 6140736 6246271 6351805
90035 5n0p9 090q4 500289 5n024 500270
rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861
500305 g0olqQo RnOq4 500280 50OP4 90027Q
21555 0pflo S826in 6138166 649701 614q239
500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP
50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q
R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4
5nnxnK srn Q gn09Q4 500n0q nnf04
gnnon
PRW flr 03W77 nArr 7
V-INFINITY = 600 KMS
T - YRS 0=
RAn 1AU
VEL q =
RAr) 3 AU
VEL n =
PAn 5 AU
Vft n = 10
PA) Atl
VFL a = PAn
20 MI VEL PAMn
5p fU VVl
00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60
56979 83199
6P5413 617524
55061 8110l
695863 617714 A1477
A61246324q76 A17P00 807 o 0
APA17 AInO
F56o A14l1
6pov7q 617AAe
7r Qt11171
61nnpQ 615RA7
80 100
10910( 134926
61340l 610860
10A043 133R4q
613R2 610047
lo7177 1st3e1
61361 11flnn
tOAgqo 1502c
A1Po n67or 611AI3940611non
e137n i155 13 flW s
AlAq0 AinIft
120 140
160656 186325
609134 607884
15057P 185236
60q2n5607Q30
1S8872 jAlrp7
600opg07aA0
157O014 IPI1r7
6flQO 008113
J-1N IRinfn
n031 6n0S6
Ierl 14Ut
6mnn An7017
160 180
211940 237538
606q36 6n6103
210895 236441
6n6072 6n6p2
Pjn130 PA5710
6n60q5 6n6940
rnnoo P34654
A7nn O9Apt
20A467 p 43Q30
A7nq1 606P7
11fn PAn I
AnSnSn AnAfl
200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240
28A637 314157
605101 604688
28753f 31305
6n510 6047n5
P6n05 619131 1193I6fl4
2897n0 i 6
65103 An311206
p4tr5 n-ins
6n9168 An4746
5nptSn A
-tpo Anq1 n AA0471
260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340
365150 3Q0628 416096 441554
6n4036 603773 6n3543 603330
364044 389521 41407 440445
6n4048 603784 603592 613348
363031 388780 41P4t5
UIQ0f
6n4nti f 61370 6n3590
An315A
3876A7 414j31n 43q41U
A1u1AOtq Aen 60n60 A1A62
IAJ61o R866P4
u1pnrq u37T 4 a
6n4n8 6fl1I 6ndeg9 A370
16un 3A611 41I-Afln
41in1
AnflnAA Anfnlp sMIn 71 6n3A
360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa
380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480
568742 594162 619579
602594 6024A3 602382
56762P 5P3o5 618466
6n29q 6n2408 6n2386
566p8f 9inf deg17719
6112603 6fn2qj6n2980
966qq 5011j9616P7
Anp6np 6P406 AnPQI
R645n 58o53 e135i
An2613
69Rn9109
R65hn qnoA=IA
6fn9613 Annl 6m Q
o 500 520
644991 67039q
602P88 61 22Nt
643R77 66q0R2
e0P2QP 6n22n9
641126 66A533
A6p295 6129oA
641035 6673140
A62paq AnP1
64degnr 666145
612311 6npois
Aqnq4n 6egna
An1 An1 7
-J 0
540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n
721206 746605
60207 601)77
720092 749412
602050 6O10O
71031R 744736
6npn0p 601ORP
71140 743S35
60n15 Anlpq
7164P7 74P31
A9nq 69t1A0
716455 74 17I
6nn6n 6nlno
600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640
707394 822784
601851 601704
79627A 82166q
601A54 6n17q7
705p4 n2024
61n186 611708
7q4 p07fl7
n 6I0t85q Anln01
70368 lP46
601n61 A1n14
7qP4k7 ct77
6118nl 60inn
660 680
84173 873559
601741 6016q0
847057 872441
6n1743 6n1692
A4Ao AviAv
6n1745 6016qu
A49n 870477
Af1747 An1A06
A4314U pAQP99
snstyn 601AO
A4lll 86R451
An19i 6 17n0
700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760
949706 975004
601559 601514
948580 97096A
60197 601516
9u7983 Q73plO
601558 AnlIr17
046618 071)09
6n11560 An 191 a
45147 07071n
6nlq6 611spl
040MA4A6158 Q68nn finICD3
7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840
1051210 1076583
601405 601372
1050091 1075466
6n1406 6n1373
ln4335 1074707
6nln7 0n1374
1048116 1073487
n14nq tnuARPn An1W76 107105
An1411 611177
10481c7 I071157
Af1012 Aflt1A
860 880
1101954 1127324
601340 601310
1100837 1126206
601342 601311
130007A 11Pq447
601141 6131P
10857 1124PP5
6n1144 6n1314
loq7961ll22q2A
601146 6n1 tq
IQA4A 1121838
An14 eniI7
900 920
1152692 1178060
6012R1 601254
1151579 117694P
6012R3 601255
1150A81 1176183
60128p3 6n1256
1j4q 3 11749qq
6nIP9 60157
11P n 1173653
6IPA6 60158
1147176 117P9916
An1 4 6019 0
940 960
1203426 1228791
601227 601202
1202308 1227673
601228 601203
12019q 12P6013
601P20 60lpo4
12003P4 122i60
601231 An6p125
xo001 12p4376
601039 6n1006
11QT899 1P21t5
6n1943 61nl9
980 1254155 601178 1253037 601179 1252277 6001180 1251051 A0f11 1 1240736 6011R2 1240519 601183 1000 1279518 601154 1278400 601155 1277640 01156 1276413 601157 1p70q6 6011RA 127181 An1O
PRW DATF 011077 PArr Is
V-TNFINITY =600 KMS
S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL
1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql
2400 3053632 600484 3052911 6n0484 30n91746 6n0484 l0fin4QA AiNn44 304010- AnnPS 104710 AftW 2900 3180302 600469 317q1ni 6n0469 1179416 6P046i5 3177167 60fn465 31776q 6noM469 17Nqvl 6nAlA6 2600 3306969 600447 3309846 6n0447 lln n] 6n044 33n183 Ann447 l300441 6n0 44 Al0Wl 6AM44 2700 3433630 6n0410 343o5nA 6n0411 A411743 6n0431 14304ql 6n04ll X4Pqnqi 6n-nAol 14PIP67 6Mnl 2800 3560289 600419 3559167 6n0419 19940P 6nnulq 3597191 Ann416 iq-q74A 6nfn416 is19in Annh16 2c)00 3686944 600401 3685821 6n04n1 36Arin97 6An4nl 368l06 Ann0n01 6AP4ni 6nn4ni1 69n9RP 6nnaop 30-00 3813597 600388 3812476 600i g IR11710 6nnARP 3stn40 Anl03PA 3PoqOiP 6fl0ARq An I01 6 n R shy3100 394n247 600175 393q126 6n0379 3918136n Afl037 3Q37108 Ann3759 T0 67 in3tqqo A n6 shy3200 4066895 6n0363 4065773 6n0i64 4069n07 6n0164 4n63799 6nn364 406P34A 6nnIA4 406m4Aq AnnMmA 4 3300 41g3940 6 00192 4192ulP 6n0353 41q1652 6n0193 419n4no 6n-nlq3 418PqAQ 60nlql 4I871 n fion l Cgt 3400 4320183 6n0342 431Q061 600147 411 95 6n0142 4117n4l 60034P u319611 6nMlu 41117A 6ftnl l 3500 4446824 6n0332 4449i70 600332 44Q36 600133 44416A3 6n0lll 444PP7 6innil 401A 6nnl l 3600 4573462 600323 4572341 6n0123 457t975 6n0121 4-i70321 fi0n03 49fiAgo 6noiP4 4r6AQQA 6mqI0 3700 4700099 6n0314 469R97A 6n0115 46Q9211 An0319 46gfi9Rf AnnII 4699ri41 6nO19 4fqNAOI0 Aftt 15 3800 4826739 6n0106 4829613 6n0306 USP4A46 6n0 0O6 482lqg3 An0WM6 UAP0177 An0IO7 4APnPUq 6nnmn7 3900 4953368 600298 4992246 6n0298 4q91480 A007qq4 Q90226 An04g Uq4PRnn 6nn0Q 404AR74 finnoaq 4000 5080000 600291 507887A 6n0291 n7811p 60091 5076857 An0p t qn943n 60nQt q071400 Annio1 4100 5206630 600284 920950A 6n0P84 Pn474P An0P94 5PO14R7 60nPA4 9pnPO0 6nnI84 900nlll Ann A4 4200 5333259 600277 5332137 600p77 9111371 6n0777 513nI16 60$0P77 3PA6Q6 Anfti77 qlA744 Fnni 8 4300 5459886 600P71 5458769 6n0271 9497998 6nnP71 9456743 6n0p71 r491PI 60ngt71 qKlArfinK ndegoV 1 4400 5586513 600269 5985391 6n0269 9qA4624 60DP6r Sr31An 600PA5 q58194A AnO61K qq7QqA- 6nnAc 4S00 5713138 600P59 571P016 6n0299 r71IP4q 60059 870Q04 O60n~qq $7A577 6nn q -i7nf6nu 6inn-Q 4600 5839761 6n0P53 583863q 6n0293 qA37871 600P3 536617 f0npqi qRj9Iqf 6n09 9PIPPI 6nn o~ 4704 5966364 600248 59)6 1262 60024a 5Q644995 6nnP4S 9503P30 Annp p qO6IRIA An0gt4A qQ9nA4A AnA 4A 480o 6093005 600243 6091881 6n0243 6n91116 6nnP43 6089A6n AnnP4q3 6nA37 66nP4 6na4R6 6nno4N 4900 6219625 600238 621R501 6nn238 6pi7717 60nP3P 6pt6461 6lOnplA Aplqnq 6nno x8 API 071 AftnOle 5000 6346245 600233 6345121 6n0213 6144$6 600P31 614310O 600P11 614167R 6nnoll Al3n6AA fitn0ll 5t00 6472863 6002P8 6471741 6n0228 647nq74 600P2A 646o71A fi00PPS f468Ql 600PQ A46Aino 600g
S 5200 6599481 600224 6998358 6n02P4 6rQ7591l 60024 69q6339 6nnPP4 Ati40na 6noP04 fi9Q9011 Ann4 530 707 606724979 6n0P20 6724P08 60npp0 672PQ91 6nnP 0 67Plr 6n0nln0 671n l~ Aftdegni9 5400 6852713 600216 68q159n 6n02t6 6A9n824 60016 694q567 A00P16 6A4914n 6nn0gt16 6n4At Ann 16 5500 6979327 60023P 697820r 6n02t2 607743A 600pip 6Q76181 6nnP12 -6q7475i4 6n0OgtIP 607p74A 6nplp
2 5600 7105941 600208 7104819 6n0208 71g409P 6no n8 71nP709 AnfnPnA 71n136A 6nnpnR 7nQ0j9A 6ftnoAR 4 - 5700 7232555 6n0204 723143P 6n0n4 7P3066t 6n0p04 7p2 QnA 60npn4 7PP7Q n 60flp05 7r 6Anln
Ir 5800 7359167 600201 7358049 6fl001 71q7P7A 600701 7356021 6nnpni 71949qgt 6nMint 199rPf 6nqgtA082 5900 7485779 6n0197 7484656 6n0ign 7483A89 finnlqA 749263P fin0nI R 7491201 6no|a 7470|A 6n~nlqn
S 6000 7612390 6n0194 7611267 600104 76|A900 6n0194 760OP43 A0njQ4 76n7814 fi0n1o4 76n971) Annin4
r PUBLICATION 77-70
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9) Compatibility of science instruments with NEP
10) Methods of calibrating science instruments for 50-yr lifetime
11) Optical vs microwave telecommunications with orbiting DSN
12) Stellar parallax measurements in deep-space
FOR STAR MISSION
For a star mission topics which warrant early study include
13) Antimatter propulsion
14) Propulsion alternatives for a star mission
15) Cryogenic spacecraft
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TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
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Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
viii
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Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
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INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
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This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
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SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
77-70
considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
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measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
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and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
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and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
77-70
Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
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A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
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around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
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A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
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300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
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TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
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If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
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MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
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MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
44
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
45
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
46
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assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
47
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system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
48
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Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
49
77-70
on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
50
77-70
70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
51
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
52
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
53
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
54
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
77-70
RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
59
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
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77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
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own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
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APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335
2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414
50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335
Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A
4478828 50P4377 5gqQ2p5 9P5471
SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980
90017P 500364 509(05650O340 500342 50033-5i
P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846
50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP
(06A6 PS4nu4A rnn668 p6qnnl
fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144
nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710
5(0it4p 360o207 7 8A 7 05 9
r00465 3811414 5lf45 1IA0S075 nn441 U0234
i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln
srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0
g0nn03 snonI
q
fnniAg onnu53
qnnil6 0n0itl
5fnlnrlq 5n014nq tfl030 q
5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839
5100 5200
5403251 5508794
500328 500322
5401959 5507502
9003P8 900322
540I015 S001PR R506r5P 900322
53qq0 5504933
qn0i9g nn0pn
K9q7469 530O
50nnxpQ 900322
59464q 550n187
3n9 5nn39
5300 5400
5614336 5719877
500316 900310
5613044 5718589
500316 500310
5612100 5717641
r00316 500310
r610479 5716016
g50n16 nn2n
W0R549 r714n85
5n0316 qnOxAl1
q6n07l4 5711PAn
5nn116 Fnn 11
5500 5600 5700 5800 5)00 6000
5829416 5930955 6036492 614P028 6247563 6353098
rn0304 50029 5002q4 50028q 500284 500279
5824124 5920663 6035200 6140736 6246271 6351805
90035 5n0p9 090q4 500289 5n024 500270
rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861
500305 g0olqQo RnOq4 500280 50OP4 90027Q
21555 0pflo S826in 6138166 649701 614q239
500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP
50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q
R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4
5nnxnK srn Q gn09Q4 500n0q nnf04
gnnon
PRW flr 03W77 nArr 7
V-INFINITY = 600 KMS
T - YRS 0=
RAn 1AU
VEL q =
RAr) 3 AU
VEL n =
PAn 5 AU
Vft n = 10
PA) Atl
VFL a = PAn
20 MI VEL PAMn
5p fU VVl
00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60
56979 83199
6P5413 617524
55061 8110l
695863 617714 A1477
A61246324q76 A17P00 807 o 0
APA17 AInO
F56o A14l1
6pov7q 617AAe
7r Qt11171
61nnpQ 615RA7
80 100
10910( 134926
61340l 610860
10A043 133R4q
613R2 610047
lo7177 1st3e1
61361 11flnn
tOAgqo 1502c
A1Po n67or 611AI3940611non
e137n i155 13 flW s
AlAq0 AinIft
120 140
160656 186325
609134 607884
15057P 185236
60q2n5607Q30
1S8872 jAlrp7
600opg07aA0
157O014 IPI1r7
6flQO 008113
J-1N IRinfn
n031 6n0S6
Ierl 14Ut
6mnn An7017
160 180
211940 237538
606q36 6n6103
210895 236441
6n6072 6n6p2
Pjn130 PA5710
6n60q5 6n6940
rnnoo P34654
A7nn O9Apt
20A467 p 43Q30
A7nq1 606P7
11fn PAn I
AnSnSn AnAfl
200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240
28A637 314157
605101 604688
28753f 31305
6n510 6047n5
P6n05 619131 1193I6fl4
2897n0 i 6
65103 An311206
p4tr5 n-ins
6n9168 An4746
5nptSn A
-tpo Anq1 n AA0471
260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340
365150 3Q0628 416096 441554
6n4036 603773 6n3543 603330
364044 389521 41407 440445
6n4048 603784 603592 613348
363031 388780 41P4t5
UIQ0f
6n4nti f 61370 6n3590
An315A
3876A7 414j31n 43q41U
A1u1AOtq Aen 60n60 A1A62
IAJ61o R866P4
u1pnrq u37T 4 a
6n4n8 6fl1I 6ndeg9 A370
16un 3A611 41I-Afln
41in1
AnflnAA Anfnlp sMIn 71 6n3A
360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa
380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480
568742 594162 619579
602594 6024A3 602382
56762P 5P3o5 618466
6n29q 6n2408 6n2386
566p8f 9inf deg17719
6112603 6fn2qj6n2980
966qq 5011j9616P7
Anp6np 6P406 AnPQI
R645n 58o53 e135i
An2613
69Rn9109
R65hn qnoA=IA
6fn9613 Annl 6m Q
o 500 520
644991 67039q
602P88 61 22Nt
643R77 66q0R2
e0P2QP 6n22n9
641126 66A533
A6p295 6129oA
641035 6673140
A62paq AnP1
64degnr 666145
612311 6npois
Aqnq4n 6egna
An1 An1 7
-J 0
540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n
721206 746605
60207 601)77
720092 749412
602050 6O10O
71031R 744736
6npn0p 601ORP
71140 743S35
60n15 Anlpq
7164P7 74P31
A9nq 69t1A0
716455 74 17I
6nn6n 6nlno
600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640
707394 822784
601851 601704
79627A 82166q
601A54 6n17q7
705p4 n2024
61n186 611708
7q4 p07fl7
n 6I0t85q Anln01
70368 lP46
601n61 A1n14
7qP4k7 ct77
6118nl 60inn
660 680
84173 873559
601741 6016q0
847057 872441
6n1743 6n1692
A4Ao AviAv
6n1745 6016qu
A49n 870477
Af1747 An1A06
A4314U pAQP99
snstyn 601AO
A4lll 86R451
An19i 6 17n0
700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760
949706 975004
601559 601514
948580 97096A
60197 601516
9u7983 Q73plO
601558 AnlIr17
046618 071)09
6n11560 An 191 a
45147 07071n
6nlq6 611spl
040MA4A6158 Q68nn finICD3
7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840
1051210 1076583
601405 601372
1050091 1075466
6n1406 6n1373
ln4335 1074707
6nln7 0n1374
1048116 1073487
n14nq tnuARPn An1W76 107105
An1411 611177
10481c7 I071157
Af1012 Aflt1A
860 880
1101954 1127324
601340 601310
1100837 1126206
601342 601311
130007A 11Pq447
601141 6131P
10857 1124PP5
6n1144 6n1314
loq7961ll22q2A
601146 6n1 tq
IQA4A 1121838
An14 eniI7
900 920
1152692 1178060
6012R1 601254
1151579 117694P
6012R3 601255
1150A81 1176183
60128p3 6n1256
1j4q 3 11749qq
6nIP9 60157
11P n 1173653
6IPA6 60158
1147176 117P9916
An1 4 6019 0
940 960
1203426 1228791
601227 601202
1202308 1227673
601228 601203
12019q 12P6013
601P20 60lpo4
12003P4 122i60
601231 An6p125
xo001 12p4376
601039 6n1006
11QT899 1P21t5
6n1943 61nl9
980 1254155 601178 1253037 601179 1252277 6001180 1251051 A0f11 1 1240736 6011R2 1240519 601183 1000 1279518 601154 1278400 601155 1277640 01156 1276413 601157 1p70q6 6011RA 127181 An1O
PRW DATF 011077 PArr Is
V-TNFINITY =600 KMS
S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL
1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql
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r PUBLICATION 77-70
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TABLE OF CONTENTS
Page
PREFACE ----------------------------------------------------- iii
ABSTRACT ------------------------------------------------------ iv
RECOMMENDATIONS FOR TECHNOLOGY DEVELOPMENT-------------------- v For Extraplanetary Mission ------------------------------------ v
First Priority ---------------------------------------------- v Second Priority v---------------------------------------------V
For Star Mission ---------------------------------------------- vi
INTRODUCTION- -------------------------------------------------- I Background- ---------------------------------------------------- I Study Objective -------------------- --------------------------- I Study Scope ------------------------------------------------- I
STUDY APPROACH ----------------------------------------------- 3 Task I 3--------------------------------------------------------3 Task 2 3--------------------------------------------------------3 Star Mission 4--------------------------------------------------4
SCIENTIFIC OBJECTIVES AND REQUIREMENTS ------------------------ 5 Scientific Objectives 5-----------------------------------------5
Primary Objectives 5------------------------------------------5 Secondary Objectives 5----------------------------------------5
Trajectory Requirements 5---------------------------------------5 Scientific Measurements- --------------------------------------- B Heliopause and Interstellar Medium-------------------------- 8 Stellar and Galactic Distance Scale ------------------------- 9 Cosmic Rays 9-------------------------------------------------9 Solar System as a Whole 0-------------------------------------10 Observations of Distant Objects ----------------------------- 10 Pluto 0-------------------------------------------------------10
Gravity Waves --------------------------------------------- 12
Advantages of Using Two Spacecraft ------------------------- 12
Simulated Stellar Encounter --------------------------------- 11
Measurements Not Planned ------------------------------------ 12
Candidate Science Payload ------------------------------------- 13
TRAJECTORIES ---------------------------------------- 14 Units and Coordinate Systems ---------------------------------- 14 Units ------------------------------------------------------- 14 Coordinate Systems ------------------------------------------ 14
Directions of Interest ---------------------------------------- 14 Extraplanetary ---------------------------------------------- 14 Pluto- ------------------------------------------------------- 15
Solar System Escape Trajectories ------------------------------ 15 Launchable Mass 15-----------------------------------------------15
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Page
TRAJECTORIES (continued) Direct Launch from Earth ------------------------------------- 18 Jupiter Assist ----------------------------------------------- 18
Jupiter Powered Flyby ------------------------------------- 25
Powered Solar Flyby -------------------------------------- 28 Low-Thrust Trajectories ---------------------------------- 28
Solar Sailing -------------------------------------------- 30 Laser Sailing ------------------------------------- 30
Laser Electric Propulsion -------------------------- 31
Fusion ------------------------------------------- ----- 32 Antimatter ------------------------------------------------- 32
Solar Plus Nuclear Electric -------------------------------- 33
Jupiter Gravity Assist ------------------------------------- 18
Launch Opportunities to Jupiter ---------------------------- 25 Venus-Earth Gravity Assist ---------------------- 28
Solar Electric Propulsion ---------------- -- --------- 31
Nuclear Electric Propulsion -------------------------------- 32
Low Thrust Plus Gravity Assist-------------------------- 32
Choice of Propulsion ----------------------------------------- 33
MISSION CONCEPT ---------------------------------------------- 38
MASS DEFINITION AND PROPULSION ------------------------------- 40
INFORMATION MANAGEMENT --------------------------------------- 44
Data Transmission Rate --------------------------------------- 46 Telemetry ---------------------------------------------------- 46
Data Coding-Considerations --------------------- 47 Tracking Loop Considerations ---------------- 47
Options -------------------------------- ---------- 50 More Power -------------------------------------------------- 50
Higher Frequencies --------------------------------------- 53
Selection of Telemetry Option -------------------------------
Data Generation ---------------------------------------------- 44 Information Management System ---------------- 44 Operations ------------------------- ------------ 45
The Telecommunication Model -------------------------------- 47 Range Equation ---------- ----------------- 47
Baseline Design ---------------------------------------------- 49 Parameters of the System ----------------------------------- 49 Decibel Table and Discussion - ----------------- 50
Larger Antennas and Lower Noise Spectral Density----------- 53
Higher Data Rates ------------------------------------ 55 55
RELATION OF THE MISSION TO SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE ----------------------------------------------- 58
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS -------------------- 59 Lifetime -------------------------------------------- 59 Propulsion and Power ----------------------------------------- 59
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Page
TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS (continued) PropulsionScience Interface --------------------------------- 60
Interaction of Thrust with Mass Measurements--------------- 61 Interaction of Thrust Subsystem with Particles and
Fields Measurements -------------------------------------- 61 Interaction of Power Subsystem with Photon Measurements ---- 61
Telecommunications ------------------------------------------- 62 Microwave vs Optical Telemetry Systems -------------------- 62 Space Cryogenics ------------------------------------------- 63 Lifetime of Telecommunications Components ------------------ 63 Baseline Enhancement vs Non-Coherent Communication
System --------------------------------------------------- 64 Information Systems ------------------------------------------ 64 Thermal Control ---------------------------------------------- 64 Components and Materials ------------------------------------ 67 Science Instruments ------------------------------------------ 67 Neutral Gas Mass Spectrometer ------------------------------- 69 Camera Field of View vs Resolution -------- ------- 69
ACKNOWLEDGEMENT ----------------------------------- ---- 71
REFERENCES ---------------------------------------------- 72
APPENDICES --------------------------------------------------- 75
Appendix A - Study Participants ------------------ 76
Appendix B - Science Contributors ---------------------------- 77
Appendix C - Thoughts for a Star Mission Study---------------- 8 Propulsion ------------------------------------------------- 78 Cryogenic Spacecraft --------------------------------------- 79 Locating Planets Orbiting Another Star --------------------- 81
Appendix D - Solar System Ballistic Escape Trajectories ------ 83
TABLES
1 Position of Pluto 1990-2030 ----------------------------- 16 2 Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU -------------- 17 3 Capabilities of Shuttle with Interim Upper Stage--------- 19 4 Solar System Escape Using Direct Ballistic Launch
from Earth -------------------------------------------- 20 5 Solar System Escape Using Jupiter Gravity Assist --------- 23 6 Jupiter Gravity Assist Versus Launch Energy -------------- 24 7 Jupiter Powered Flyby ------------------------------- 26 8 Launched Mass for 300 kg Net Payload After Jupiter
Powered Flyby ------------------------------------------ 27 9 Powered Solar Flyby -------------------------------------- 29 10 Performance of Ultralight Solar Sails -------------------- 35
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Page
TABLES (continued)
11 Mass and Performance Estimates for Baseline System - 43 12 Baseline Telemetry at 1000 AU ----------------- 52 13 Optical Telemetry at 1000 AU -------------------------- 54 14 Telemetry Options ------------------------ 56 15 Proposed Data Rates -------------------------------------- 57 16 Thermal Control Characteristics of Extraplanetary
Missions ----------------------------------------------- 66 17 Technology Rdquirements for Components amp Materials 68
FIGURES
1 Some Points of Interest on the Celestial Map ------------ 7 2 Geometry of Jupiter Flyby -------------------- 21 3 Solar System Escape with Ultralight Solar Sails ---------- 34 4 Performance of NEP for Solar Escape plus Pluto ----------- 41 5 Data Rate vs Ratio of Signal Power to Noise Spectral
Power Density ------------------------------------------ 51
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INTRODUCTION
BACKGROUND
Even before the first earth satellites were launched in 1957 there
was popular interest in the possibility of spacecraft missions to other
stars and their planetary systems As space exploration has progressed
to the outer planets of the solar system it becomes appropriate to begin
to consider the scientific promise and engineering difficulties of mission
to the stars and hopefully their accompanying planets
In a conference on Missions Beyond the Solar System organized by
L D Friedman and held at JPL in August 1976 the idea of a precursor
mission out beyond the planets but not nearly to another star was
suggested as a means of bringing out and solving the engineering proshy
blems that would be faced in a mission to a star At the same time it
was recognized that such a precursor mission even though aimed primarily
at engineering objectives should also have significant scientific objecshy
tives
Subsequently in November 1976 this small study was initiated to
examine a precursor mission and identify long lead-time technology developshy
ment which should be initiated to permit such a mission This study was
funded by the Study Analysis and Planning Office (Code RX) of the NASA
Office of Aeronautics and Space Technology
STUDY OBJECTIVE
The objective of the study was to establish probable science goals
mission concepts and technology requirements for a mission extending from
outer regions of the solar system to interstellar flight An unmanned
mission was intended
STUDY SCOPE
The study was intended to address science goals mission concepts
and technology requirements for the portion of the mission outward from
the outer portion of the planetary system
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Because of the limited funding available for this study it was
originally planned that the portion of the mission between the earth
and the outer portion of the planetary system would not be specifically
addressed likewise propulsion concepts and technology would not be
included Problems encountered at speeds approaching that of light were
excluded for the same reason In the course of the study it became
clear that these constraints were not critical and they were relaxed
as indicated later in this report
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STUDY APPROACH
The study effort consisted of two tasks Task 1 concerned science
goals and mission concepts Task 2 technology requirements
TASK I
In Task 1 science goals for the mission were to be examined and
the scientific measurements to be made Possible relation of the mission
to the separate effort on Search for Extraterrestrial Intelligence was
also to be considered Another possibility to be examined was that of
using the data in reverse time sequence to examine a star and its surshy
roundings (in this case the solar system) as might be done from an
approaching spacecraft
Possible trajectories would be evaluated with respect to the intershy
action of the direction of the outward asymptote and the speed with the
science goals A very limited examination might be made of trajectories
within the solar system and accompanying propulsion concepts to assess
the feasibility of the outward velocities considered
During the study science goals and objectives were derived by series
of conversations and small meetings with a large number of scientists
Most of these were from JPL a few elsewhere Appendix B gives their
names
The trajectory information was obtained by examination of pertinent
work done in other studies and a small amount of computation carried out
specifically for this study
TASK 2
In this task technology requirements that appear to differ signishy
ficantly from those of missions within the solar system were to be identishy
fied These would be compared with the projected state-of-the-art for
the year 2000 plusmn 15 It was originally planned that requirements associated
with propulsion would be addressed only insofar as they interact with power
or other systems
3
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This task was carried out by bringing together study team particishy
pants from each of the technical divisions of the Laboratory (Particishy
pants are listed in Appendix A-) Overal-i concepts were developed and
discussed at study team meetings Each participant obtained inputs from
other members of his division on projected capabilities and development
needed for individual subsystems These were iterated at team meetings
In particular several iterations were needed between propulsion and trashy
jectory calculations
STAR MISSION
Many of the contributors to this study both scientific and engineershy
ing felt an actual star mission should be considered Preliminary examshy
ination indicated however that the hyperbolic velocity attainable for
solar system escape during the time period of interest (year 2000 plusmn 15)
was of the order of 102 kms or 3 x 109 kmyear Since the nearest star 013
is at a distance of 43 light years or about 4 x 10 km the mission durshy
ation would exceed 10000 years This did not seem worth considering for
two reasons
First attaining and especially establishing a spacecraft lifeshy
time of 10000 years by the year 2000 is not considered feasible Secondly
propulsion capability and hence hyperbolic velocity attainable is expected
to increase with time Doubling the velocity should take not more than
another 25 years of work and would reduce the mission duration to only
5000 years Thus a spacecraft launched later would be expected to arrive
earlier Accordingly launch to a star by 2000 plusmn 15 does not seem reasonable
For this reason a star mission is not considered further in the body
of this report A few thoughts which arose during this study and pertain
to a star mission are recorded in Appendix C It is recommended that a
subsequent study address the possibility of a star mission starting in
2025 2050 or later and the long lead-time technology developments that
will be needed to permit this mission
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SCIENTIFIC OBJECTIVES AND REQUIREMENTS
Preliminary examination of trajectory and propulsion possibilities
indicated that a mission extending to distances of some hundred or pershy
haps a few thousand AU from the sun with a launch around the year 2000
was reasonable The following science objectives and requirements are
considered appropriate for such a mission
SCIENTIFIC OBJECTIVES
Primary Objectives
1) Determination of the characteristics of the heliopause where the
solar wind presumably terminates against the incoming interstellar
medium
2) Determination of the characteristics of the interstellar medium
3) Determination of the stellar and galactic distance scale through
measurements of the distance to nearby stars
4) Determination of the characteristics of cosmic rays at energies
excluded by the heliosphere
5) Determination of characteristics of the solar system as a whole
such as its interplanetary gas distribution and total mass
Secondary Objectives
i) Determination of the characteristics of Pluto and its satellites
and rings if any If there had been a previous mission to Pluto
this objective would be modified
2) Determination of the characteristics of distant galactic and extrashy
galactic objects
3) Evaluation of problems of scientific observations of another solar
system from a spacecraft
TRAJECTORY REQUIREMENTS
The primary science objectives necessitate passing through the helioshy
pause preferably in a relatively few years after launch to increase the
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reliability of data return Most of the scientists interviewed preferred
a mission directed toward the incoming interstellar gaswhere the helioshy
pause is expected to be closest and most well defined The upwind
direction with respect to neutral interstellar gas is approximately RA
250 Decl - 160 (Weller and Meier 1974 Ajello 1977) (See Fig 1
The suns motion with respect to interstellar charged particles and magshy
netic fields is not known) Presumably any direction within say 400
of this would be satisfactory A few scientists preferred a mission
parallel to the suns axis (perpendicular to the ecliptic) believing
that interstellar magnetic field and perhaps particles may leak inward
further along this axis Some planetary scientists would like the misshy
sion to include a flyby or orbiter of Pluto depending on the extent to which
Pluto might have been explored by an earlier mission Although a Pluto flyby
is incompatible with a direction perpendicular to the ecliptic it happens
that in the period of interest (arrival around the year 2005) Pluto will
lie almost exactly in the upwind direction mentioned so an upwind
trajectory could include a Pluto encounter
The great majority of scientists consulted preferred a trajectory
that would take the spacecraft out as fast as possible This would minishy
mize time to reach the heliopause and the interstellar medium Also it
would at any time provide maximum earth-SC separation as a base for
optical measurements of stellar parallax A few scientists would like
to have the SC go out and then return to the solar system to permit
evaluating and testing methods of obtaining scientific data with a
future SC encountering another solar system Such a return would
roughly halve the duration of the outward portion of the flight for
any fixed mission duration Also since considerable propulsive energy
would be required to stop and turn around this approach would conshy
siderably reduce the outward hyperbolic velocity attainable These two
effects would greatly reduce the maximum distance that could be reached
for a given mission duration
As a strawman mission it is recommended that a no-return trajecshy
tory with an asymptote near RA 2500 Decl -15o and a flyby of Pluto be
6
90 I 11
60 - BARNARDS 380000 AU
30-
STAR
APEX OF SOLAR MOTION RELATIVE TO NEARBY STARS
YEAR 2000 30 AU
z o
1990-30 30 AU
0 CELESTIAL EQUATOR
uj
0
INCOMING INTERSTELLAR GAS R-30GWELLER AND MEIER (1974)2010AJErLLO (1977)
C
-60 -2
-90 360
2 34 AU
300 240
- a C N A RNaCN UR 270000 AU
180 120 60 0
RIGHT ASCENSION (0)
Fig I Some Points of Interest on the Celestial Map From Sergeyevsky (1971) modified
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considered with a hyperbolic excess velocity of 40-90 kms or more
Higher velocities should be used if practical Propulsion should be
designed to avoid interference with scientific measurements and should
be off when mass measurements are to be made
A number of scientific observations (discussed below) would be
considerably improved if two spacecraft operating simultaneously were
used with asymptotic trajectories at approximately right angles to
each other Thus use of a second spacecraft with an asymptotic tra3ecshy
tory approximately parallel to the solar axis is worthwhile scientifically
SCIENTIFIC MEASUREMENTS
Heliopause and Interstellar Medium
Determination is needed of the characteristics of the solar wind
just inside the heliopause of the heliopause itself of the accompanying
shock (if one exists) and of the region between the heliopause and the
shock The location of the heliopause is not known estimates now tend
to center at about 100 AU from the sun (As an indication of the uncershy
tainty estimates a few years ago ran as low as 5 AU)
Key measurements to be made include magnetic field plasma propershy
ties (density velocity temperature composition plasma waves) and
electric field Similar measurements extending to low energy levels
are needed in the interstellar medium together with measurements of the
properties of the neutral gas (density temperature composition of atomic
and molecular species velocity) and of the interstellar dust (particle
concentration particle mass distribution composition velocity) The
radiation temperature should also be measured
The magnetic electric and plasma measurements would require only
conventional instrumentation but high sensitivity would be needed Plasma
blobs could be detected by radio scintillation of small sources at a waveshy
length near 1 m Radiation temperature could be measured with a radiomshy
eter at wavelengths of 1 cm to 1 m using a detector cooled to a few
Kelvins Both in-situ and remote measurements of gas and dust properties
are desirable In-situ measurements of dust composition could be made
8
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by an updated version of an impact-ionization mass spectrometer In-situ
measurements of ions could be made by a mass spectrometer and by a plasma
analyzer In-situ measurements of neutral gas composition would probably
require development of a mass spectrometer with greater sensitivity and
signalnoise ratio than present instruments Remote measurements of gas
composition could be made by absorption spectroscopy looking back toward
the sun Of particular interest in the gas measurements are the ratios 1HHHHeletecnetofN0adifpsbe+HH2H+ and if possible ofDi HeH He3He4 the contents of C N
Li Be B and the flow velocity Dust within some size range could be
observed remotely by changes in the continuum intensity
Stellar and Galactic Distance Scale
Present scales of stellar and galactic distance are probably uncershy
tain by 20 This in turn leads to uncertainties of 40 in the absolute
luminosity (energy production) the quantity which serves as the fundashy
mental input data for stellar model calculations Uncertainties in galactic
distances make it difficult to provide good input data for cosmological
models
The basic problem is that all longer-range scales depend ultimately
on the distances to Cepheid variables in nearby clusters such as the
Hyades and Pleiades Distances to these clusters are determined by stashy
tistical analysis of relative motions of stars within the clusters and
the accuracy of this analysis is not good With a baseline of a few
hundred AU between SC and earth triangulation would provide the disshy
tance to nearby Cepheids with high accuracy This will require a camera
with resolution of a fraction of an arc second implying an objective
diameter of 30 cm to 1 m Star position angles need not be measured
relative to the sun or earth line but only with respect to distant
stars in the same image frame To reduce the communications load only
the pixel coordinates of a few selected objects need be transmitted to
earth
Cosmic Rays
Measurements should be made of low energy cosmic rays which the
solar magnetic field excludes from the heliosphere Properties to be
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measured include flux spectrum composition and direction Measurements
should be made at energies below 10 MeV and perhaps down to 10 keV or
lower Conventional instrumentation should be satisfactory
Solar System as a Whole
Determinations of the characteristics of the solar system as a
whole include measurements of neutral and ionized gas and of dust Quanshy
tities to be measured include spatial distribution and the other propershy
ties mentioned above
Column densities of ionized material can be observed by low freshy
quency radio dispersion Nature distribution and velocity of neutral
gas components and some ions can be observed spectroscopically by fluoresshy
cence under solar radiation To provide adequate sensitivity a large
objective will be needed Continuum observation should show the dust
distribution
The total mass of the solar system should be measured This could
be done through dual frequency radio doppler tracking
Observations of Distant Objects
Observations of more distant objects should include radio astronomy
observations at frequencies below 1 kHz below the plasma frequency of the
interplanetary medium This will require a VLF receiver with a very long
dipole or monopole antenna
Also both radio and gamma-ray events should be observed and timed
Comparison of event times on the SC and at earth will indicate the direcshy
tion of the source
In addition the galactic hydrogen distribution should be observed
by UV spectrophotometry outside any local concentration due to the sun
Pluto
If a Pluto flyby is contemplated measurements should include optical
observations of the planet to determine its diameter surface and atmosshy
phere features and an optical search for and observations of any satellites
or rings Atmospheric density temperature and composition should be measured
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and nearby charged particles and magnetic fields Surface temperature and
composition should also be observed Suitable instruments include a TV
camera infrared radiometer ultravioletvisible spectrometer particles
and fields instruments infrared spectrometer
For atmospheric properties UV observations during solar occultation
(especially for H and He) and radio observations of earth occultation should
be useful
The mass of Pluto should be measured radio tracking should provide
this
If a Pluto orbiter is included in the mission measurements should
also include surface composition variable features rotation axis shape
and gravity field Additional instruments should include a gamma-ray
spectrometer and an altimeter
Simulated Stellar Encounter
If return to the solar system is contemplated as a simulation of a
stellar encounter observations should be made during approach of the
existence of possible stellar companions and planets and later of satelshy
lites asteroids and comets and of their characteristics Observations
of neutral gas dust plasma and energetic emissions associated with the
star should be made and any emissions from planets and satellites Choice(s)
should be made of a trajectory through the approaching solar system (recog-_
nizing the time-delays inherent in a real stellar mission) the choice(s)
should be implemented and flyby measurements made
The approach measurements could probably be made using instruments
aboard for other purposes For flyby it would probably be adequate to
use data recorded on earlier missions rather than carry additional instrushy
ments
An alternative considered was simulating a stellar encounter by
looking backwards while leaving the solar system and later replaying
the data backwards This was not looked on with favor by the scientists
contacted because the technique would not permit making the operational
decisions that would be key in encountering a new solar system locating
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and flying by planets for example Looking backwards at the solar system
is desired to give solar system data per se as mentioned above Stellar
encounter operations are discussed briefly in Appendix C
Gravity Waves
A spacecraft at a distance of several hundred AU offers an opportunity
for a sensitive technique for detecting gravity waves All that is needed
is precision 2-way radio doppler measurements between SC and earth
Measurements Not Planned
Observations not contemplated include
1) Detecting the Oort cloud of comets if it exists No method of
detecting a previously unknown comet far out from the sun is recogshy
nized unless there is an accidental encounter Finding a previously
seen comet when far out would be very difficult because the nrbits
of long-period comets are irregular and their aphelia are hard to
determine accurately moreover a flyby far from the sun would
tell little about the comet and nothing about the Oort cloud The
mass of the entire Oort cloud might be detectable from outside but
the mission is not expected to extend the estimated 50000 AU out
If Lyttletons comet model is correct a comet accidentally encounshy
tered would be revealed by the dust detector
2) VLBI using an earth-SC baseline This would require very high rates
of data transmission to earth rates which do not appear reasonable
Moreover it is doubtful that sources of the size resolved with
this baseline are intense enough to be detected and that the reshy
quired coherence would be maintained after passage through inhomoshy
geneities in the intervening medium Also with only 2 widely
separated receivers and a time-varying baseline there would be
serious ambiguity in the measured direction of each source
Advantages of Using Two Spacecraft
Use of two spacecraft with asymptotic trajectories at roughly right
angles to each other would permit exploring two regions of the heliopause
12
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(upwind and parallel to the solar axis) and provide significantly greater
understanding of its character including the phenomena occurring near the
magnetic pole direction of the sun Observations of transient distant
radio and gamma-ray events from two spacecraft plus the earth would permit
location of the source with respect to two axes instead of the one axis
determinable with a single SC plus earth
CANDIDATE SCIENCE PAYLOAD
1) Vector magnetometer
2) Plasma spectrometer
3) Ultravioletvisible spectrometers
4) Dust impact detector and analyzer
5) Low energy cosmic ray analyzer
6) Dual-frequency radio tracking (including low frequency with high
frequency uplink)
7) Radio astronomyplasma wave receiver (including VLF long antenna)
8) Massspectrometer
9) Microwave radiometer
10) Electric field meter
11) Camera (aperture 30 cm to 1 m)
12) Gamma-ray transient detector
If Pluto flyby or orbiter is planned
13) Infrared radiometer
14) Infrared spectrometer
If Pluto orbiter is planned
15) Gamma-ray spectrometer
16) Altimeter
13
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TRAJECTORIES
UNITS AND COORDINATE SYSTEMS
Units
Some useful approximate relations in considering an extraplanetary
mission are
1 AU = 15 x 108km
1 light year = 95 x 1012 km = 63 x 104 AU
1 parsec = 31 x 10 1km = 21 x 105 AU = 33 light years
1 year = 32 x 107
- 61 kms = 021 AUyr = 33 x 10 c
where c = velocity of light
Coordinate Systems
For objects out of the planetary system the equatorial coordinshy
ate system using right ascension (a) and declination (6) is often more
convenient than the ecliptic coordinates celestial longitude (X)
and celestial latitude (8) Conversion relations are
sin S = cos s sin 6- sin s cos 6 sin a
cos 8 sin X = sin c sin 6 +cos 6 cos amp sin a
CoS Cos A = Cos amp Cos a
where s = obliquity of ecliptic = 2350
DIRECTIONS OF INTEREST
Extraplanetary
Most recent data for the direction of the incoming interstellar
neutral gas are
Weller amp Meier (1974)
Right ascension a = 2520
Declination 6 = -15
Ajello (1977) deg Right ascension a = 252
Declination 6 = -17
14
77-70
Thus these 2 data sources are in excellent agreement
At a = 2500 the ecliptic is about 200S of the equator so the wind
comes in at celestial latitude of about 4 Presumably it is only
a coincidence that this direction lies close to the ecliptic plane
The direction of the incoming gas is sometimes referred to as the
apex of the suns way since it is the direction toward which the sun
is moving with respect to the interstellar gas The term apex howshy
ever conventionally refers to the direction the sun is moving relative
to nearby stars rather than relative to interstellar gas These two
directions differ by about 450 in declination and about 200 in right
ascension The direction of the solar motion with respect to nearby
stars and some other directions of possible interest are shown in
Fig 1
Pluto
Table 1 gives the position of Pluto for the years 1990 to 2030
Note that by coincidence during 2000 to 2005 Pluto is within a few
degrees of the direction toward the incoming interstellar gas (see Fig 1)
At the same time it is near its perihelion distance only 30-31 AU
from the sun
SOLAR SYSTEM ESCAPE TRAJECTORIES
As a step in studying trajectories for extraplanetary missions a
series of listings giving distance and velocity vs time for parabolic
and hyperbolic solar system escape trajectories has been generated These
are given in Appendix D and a few pertinent values extracted in Table 2
Note for example that with a hyperbolic heliocentric excess velocity
V = 50 kms a distance of 213 AU is reached in 20 years and a distance
of 529 AU in 50 years With V = 100 kms these distances would be
doubled approximately
LAUNCHABLE MASS
Solar system escape missions typically require high launch energies
referred to as C3 to achieve either direct escape or high flyby velocity
15
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TABLE 1
Position of Pluto 1990-2030
Position on 1 January
Distance Right Declination from ascension sun
Year AU 0 0
1990 2958 22703 -137 1995 2972 23851 -630 2000 3012 24998 -1089 2005 2010
3078 3164
26139 27261
-1492 -1820
2015 3267 28353 -2069 2020 3381 29402 -2237 2025 3504 30400 -2332 2030 3631 31337 -2363
16
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TABLE 2
Summary of Solar System Ballistic Escape Trajectories
Initial Condition Circular Orbit at 1 AU
V Distance (RAD) AU Velocity (VEL) las for Time (T) = for Time (T) =
kms 10 yrs 20 yrs 50 yrs 10 yrs 20 yrs 50 yrs
0 251 404 753 84 66 49 1 252 406 760 84 67 49 5 270 451 904 95 80 67
10 321 570 126 125 114 107 20 477 912 220 209 205 202 30 665 130 321 304 302 301 40 865 171 424 403 401 401 50 107 213 529 502 501 500 60 128 254 634 601 601 600
(See Appendix D for detail)
17
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at a gravity assist planet Table 3 gives projected C3 capabilities
in (kms)2 for the three versions of the ShuttleInterim Upper Stage
assuming net payloads of 300 400 and 500 kg It can be seen that as
launched mass increases the maximum launch energy possible decreases
Conceivably higher C3 are possible through the use of in-orbit
assembly of larger IUS versions or development of more powerful upper
stages such as the Tug The range of C3 values found here will be used
in the study of possible escape trajectories given below
DIRECT LAUNCH FROM EARTH
Direct launch from the Earth to a ballistic solar system escape
trajectory requires a minimum launch energy of 1522 (cms) 2 Table 4
gives the maximum solar system V obtainable (in the ecliptic plane) and
maximum ecliptic latitude obtainable (for a parabolic escape trajectory)
for a range of possible C3
The relatively low V and inclination values obtainable with direct
launch make it an undesirable choice for launching of extra-solar
probes as compared with those techniques discussed below
JUPITER ASSIST
Jupiter Gravity Assist
Of all the planets Jupiter is by far the best to use for gravity
assisted solar system escape trajectories because of its intense gravity
field The geometry of the Jupiter flyby is shown in Figure 2 Assume
that the planet is in a circular orbit about the Sun with orbital
velocity VJh = 1306 kms
The spacecraft approaches the planet with some relative velocity
Vin directed at an angle 0 to VJh and departs along Vout after having
been bent through an angle a The total bend angle
2 a = 2 arcsin [1(I + V r p)]in p
where r is the closest approach radius to Jupiter and v= GMJ the P
gravitational mass of Jupiter Note that VJh Vin and Vout need not all
18
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TABLE 3
Capabilities of Shuttle with Interim Upper Stage
Launch energy C3
(kms) 2
for indicated
payload (kg)
Launch Vehicle 300 400 500
Shuttle2-stage IUS 955 919 882
Shuttle3-stage IUS 1379 1310 1244
Shuttle4-stage IUS 1784 1615 1482
19
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TABLE 4
Sblar System Escape Using Direct Ballistic Launch from Earth
Launch energy C3
(kms)2
1522
155
160
165
170
175
Maximum hyperbolic excess velocity V in ecliptic plane
(kms)
000
311
515
657
773
872
Maximum ecliptic latitude Max for parabolic trajectory
(0)
000
273
453
580
684
774
20
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A
v escape
~VA h
Fig 2 Geometry of Jupiter Flyby
21
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be in the same plane so the spacecraft can approach Jupiter in the
ecliptic plane and be ejected on a high inclination orbit The helioshy
centric velocity of the spacecraft after the flyby Vsh is given by the
vector sum of VJh and Vou If this velocity exceeds approximatelyt
1414 VJh shown by the ampashed circle in Figure 2 the spacecraft
achieves by hyperbolic orbit and will escape the solar system The
hyperbolic excess velocity is given by V2sh - 2pr where V here is GMs
the gravitation mass for the Sun and r is the distance from the Sun
52 astronomical units The maximum solar system escape velocity will
be obtained when the angle between V and Vout is zero This will
necessarily result in a near-zero inclination for the outgoing orbit
Around this vector will be a cone of possible outgoing escape trajecshy
tories As the angle from the central vector increases the hyperbolic
excess velocity relative to the Sun will decrease The excess velocity
reaches zero (parabolic escape orbit) when the angle between VJh and
Vsh is equal to arc cos [(3 - V2 inV 2 Jh)2 2 This defines then the
maximum inclination escape orbit that can be obtained for a given Vin at Jupiter Table 5 gives the dependence of solar system hyperbolic
escape velocity on V and the angle between V and Vs The maximumin Jh s angle possible for a given V is also shownin
For example for a V at Jupiter of 10 kms the maximum inclinashyin tion obtainable is 3141 and the solar system escape speed will be
1303 kms for an inclination of 100 1045 kms for an inclination of
20 Note that for V s greater than 20 kms it is possible to ejectin
along retrograde orbits This is an undesirable waste of energy however
It is preferable to wait for Jupiter to move 1800 around its orbit when
one could use a direct outgoing trajectory and achieve a higher escape
speed in the same direction
To consider in more detail the opportunities possible with Jupiter
gravity assist trajectories have been found assuming the Earth and
Jupiter in circular co-planar orbits for a range of possible launch
energy values These results are summarized in Table 6 Note that the
orbits with C3 = 180 (kms)2 have negative semi-major axes indicating
that they are hyperbolic With the spacecraft masses and launch vehicles
discussed above it is thus possible to get solar syst6m escape velocities
22
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TABLE 5
Solar System Escape Using Jupiter Gravity Assist
Approach velocity relative to JupiterVin (kms) 60 100 150 200 250 300
Angle between outbound heliocentric velocity of SC Vsh and of Jupiter Jsh Solar system hyperbolic excess velocity V (kms)
(0) for above approach velocity
00 470 1381 2112 2742 3328 3890 50 401 1361 2100 2732 3319 3882
100 1303 2063 2702 3293 3858 150 1200 2001 2653 3250 3819 200 1045 1913 2585 3191 3765 250 812 1799 2497 3116 3697 300 393 1657 2391 3025 3615 400 1273 2125 2801 3413 500 647 1789 2528 3169 600 1375 2213 2892 700 832 1865 2594 800 1486 2283
900 1065 1970
Maximum angle between outbound heliocentric velocity of SC Vsh and of Jupiter Vjh() for above approach velocity
958 3141 5353 7660 10357 14356
Note indicates unobtainable combination of V and anglein
23
TABLE 6
Jupiter Gravity Assist versus Launch Energy
Launch Energy
C3 2 (kns)
Transfer orbit semi-major axis
(AU)
Approach velocity relative to Jupiter Vin (kms)
Angle between approach velocity and Jupiter heliocentric velocitya
((0)
Maximum Maximum Maximum heliocentric inclination bend hyperbolic to ecliptic angle escape for parabolic relative to velocity trajectory Jupiter a Vw for Xmax for
for flyby flyby at flyby at at 11 R 11 R 11 R
(0) (0)
00 900
1000 1100 1200 1300 1400 1500 1600 1800 2000
323 382 463 582 774
1138 2098
11743 -3364 -963 -571
655 908
1098 1254 1388 1507 1614 1712 1803 1967 2113
14896 12734 11953 11510 11213 10995 10827 10691 10578 10399 10261
15385
14410 13702 13135 12659 12248 11886 11561 11267 10752 10311
659
1222 1538 1772 1961 2121 2261 2387 2501 2702 2877
1366
2717 3581 4269 4858 5382 5861 6305 6722 7499 8222
D
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on the order of 25 kms in the ecliptic plane and inclinations up to
about 670 above the ecliptic plane using simple ballistic flybys of
Jupiter Thus a large fraction of the celestial sphere is available
to solar system escape trajectories using this method
Jupiter Powered Flyby
One means of improving the performance of the Jupiter flyby is to
perform a maneuver as the spacecraft passes through periapsis at Jupishy
ter The application of this AV deep in the planets gravitational
potential well results in a substantial increase in the outgoing Vout
and thus the solar system hyperbolic excess velocity V This technique
is particularly useful in raising relatively low Vin values incoming
to high outgoing Vouts Table 7 gives the outgoing Vou t values at
Jupiter obtainable as a function of V and AV applied at periapsisin
A flyby at 11 R is assumed The actual Vou t might be fractionally smaller
because of gravity losses and pointing errors but the table gives a
good idea of the degrees of performance improvement possible
Carrying the necessary propulsion to perform the AV maneuver would
require an increase in launched payload and thus a decrease in maximum
launch energy and V possible at Jupiter Table 8 gives the requiredin launched mass for a net payload of 300 kg after the Jupiter flyby using
a space storable propulsion system with I of 370 seconds and the sp maximum C3 possible with a Shuttle4-stage IUS launch vehicle as a
function of AV capability at Jupiter These numbers may be combined
with the two previous tables to find the approximate V at Jupiter and In
the resulting Vout
Launch Opportunities to Jupiter
Launch opportunities to Jupiter occur approximately every 13 months
Precise calculations of such opportunities would be inappropriate at
this stage in a study of extra-solar probe possibilities Because
Jupiter moves about 330 in ecliptic longitude in a 13 month period and
because the cone of possible escape trajectories exceeds 300 in halfshy
width for V above about 10 kms it should be possible to launch out
to any ecliptic longitude over a 12 year period by properly choosing
the launch date and flyby date at Jupiter With sufficient V the out
25
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TABLE 7
Jupiter Powered Flyby
Approach velocity relative toJupaie to Outbound velocity relative to Jupiter VoJupiter Vin (kns) for indicated AV (kms) applied
at periapsis of 11 R
50 100 150 200 250
60 966 1230 1448 1638 1811 80 1103 1341 1544 1725 1890
100 1257 1471 1659 1829 1986 120 1422 1616 1700 1950 2099 140 1596 1772 1933 2083 2224
160 1776 1937 2086 2237 2361 180 1959 2108 2247 2380 2506 200 2146 2283 2414 2539 2600
26
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TABLE 8
Launched Mass for 300 kg Net Payload
after Jupiter Powered Flyby
AV at Required launched mass Jupiter for SC Is = 370 s
p
(kms) (kg)
0 300
5 428
10 506
15 602
20 720
25 869
Maximum launch energy C3 attainable with shuttle4-stage IUS
(kms) 2
1784
1574
1474
1370
1272
1149
27
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high ecliptic latitudes would be available as described in an earlier
section Flight times to Jupiter will typically be 2 years or less
Venus-Earth Gravity Assist
One means of enhancing payload to Jupiter is to launch by way of
a Venus-Earth Gravity Assist (VEGA) trajectory These trajectories 2
launch at relatively low C3 s 15 - 30 (kms) and incorporate gravity
assist and AV maneuvers at Venus and Earth to send large payloads to
the outer planets The necessary maneuvers add about 2 years to the
total flight time before reaching Jupiter The extra payload could
then be used as propulsion system mass to perform the powered flyby
at Jupiter An alternate approach is that VEGA trajectories allow use
of a smaller launch vehicle to achieve the same mission as a direct
trajectory
POWERED SOLAR FLYBY
The effect of an impulsive delta-V maneuver when the spacecraft is
close to the Sun has been calculated for an extra-solar spacecraft The
calculations are done for a burn at the perihelion distance of 01 AU
for orbits whose V value before the burn is 0 5 and 10 lans respectiveshy
ly Results are shown in Table 9 It can be seen that the delta-V
maneuver deep in the Suns potential well can result in a significant
increase in V after the burn having its greatest effect when the preshy
burn V is small
The only practical means to get 01 from the Sun (other than with a
super sail discussed below) is a Jupiter flyby at a V relative to
Jupiter of 12 kms or greater The flyby is used to remove angular
momentum from the spacecraft orbit and dump it in towards the Sun
The same flyby used to add energy to the orbit could achieve V of 17
kms or more without any delta-V and upwards of 21 kms with 25 kms
of delta-V at Jupiter The choice between the two methods will require
considerably more study in the future
LOW-THRUST TRAJECTORIES
A large number of propulsion techniques have been proposed that do
not depend upon utilization of chemical energy aboard the spacecraft
28
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TABLE 9
Powered Solar Flyby
AV Heliocentric hyperbolic excess velocity V (kms) (kms) after burn 01 AU from Sun and initial V as indicated (kms)
0 5 10
1 516 719 1125
3 894 1025 1342
5 1155 1259 1529
10 1635 1710 1919
15 2005 2067 2242
20 2317 2371 2526
25 2593 2641 2782
29
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Among the more recent reviews pertinent to this mission are those
by Forward (1976) Papailiou et al (1975) and James et al (1976) A
very useful bibliography is that of Mallove et al (1977)
Most of the techniques provide relative low thrust and involve long
periods of propulsion The following paragraphs consider methods that
seem the more promising for an extraplanetary mission launched around
2000
Solar Sailing
Solar sails operate by using solar radiation pressure to add or
subtract angular momentum from the spacecraft (Garwin 1958) The
basic design considered in this study is a helio-gyro of twelve
6200-meter mylar strips spin-stabilized
According to Jerome Wright (private communication) the sail is
capable of achieving spacecraft solar system escape velocities of 15-20
kms This requires spiralling into a close orbit approximately 03 AU
from the sun and then accelerating rapidly outward The spiral-in
maneuver requires approximately one year and the acceleration outward
which involves approximately 1-12 - 2 revolutions about the sun
takes about 1-12 - 2 years at which time the sailspacecraft is
crossing the orbit of Mars 15 AU from the sun on its way out
The sail is capable of reaching any inclination and therefore any
point of the celestial sphere This is accomplished by performing a
cranking maneuver when the sail is at 03 AU from the sun before
the spiral outward begins The cranking maneuver keeps the sail in a
circular orbit at 03 AU as the inclination is steadily raised The
sail can reach 900 inclination in approximately one years time
Chauncey Uphoff (private communication) has discussed the possishy
bility of a super sail capable of going as close as 01 AU from the sun
and capable of an acceleration outward equal to or greater than the
suns gravitational attraction Such a sail might permit escape Vs
on the order of 100 kms possible up to 300 kms However no such
design exists at present and the possibility of developing such a sail
has not been studied
Laser Sailing
Rather et al (1976) have recently re-examined the proposal (Forshy
ward 1962 Marx 1966Moeckle 1972) of using high energy lasers rather
than sunlight to illuminate a sail The lasers could be in orbit
30
77-70
around the earth or moon and powered by solar collectors
Rather et al found that the technique was not promising for star
missions but could be useful for outer planet missions Based on their
assumptions a heliocentric escape velocity of 60 Ios could be reached
with a laser output power of about 30 kW 100 kms with about 1500 kW
and 200 Ims with 20 MW Acceleration is about 035 g and thrusting
would continue until the SC was some millions of kilometers from earth
Solar Electric Propulsion
Solar electric propulsion uses ion engines where mercury or
other atoms are ionized and then accelerated across a potential gap
to a very high exhaust velocity The electricity for generating the
potential comes from a large solar cell array on the spacecraft
Current designs call for a 100 kilowatt unit which is also proposed
for a future comet rendezvous mission A possible improvement to the
current design is the use of mirror concentrators to focus additional
sunlight on the solar cells at large heliocentric distances
According to Carl Sauer (private communication) the solar powered
ion drive is capable of escape Vs on the order of 10-15 kms in the
ecliptic plane Going out of the ecliptic is more of a problem because
the solar cell arrays cannot be operated efficiently inside about 06 AU
from the sun Thus the solar electric drive cannot be operated
close iiito the sun for a cranking maneuver as can the solar sail
Modest inclinations can still be reached through slower cranking or the
initial inclination imparted by the launch vehicle
Laser Electric Propulsion
An alternative to solar electric propulsion is laser electric
lasers perhaps in earth orbit radiate power to the spacecraft which is
collected and utilized in ion engines The primary advantage is that
higher energy flux densities at the spacecraft are possible This would
permit reducing the receiver area and so hopefully the spacecraft
weight To take advantage of this possibility receivers that can
operate at considerably higher temperatures than present solar cells will
be needed A recent study by Forward (1975) suggests that a significant
performance gain as compared to solar electric may be feasible
6 2 Rather et al assumed an allowable flux incident on the sail of 10 Wm laser wavelength 05 pm and laser beam size twice-the diffraction limit For this calculation 10 km2 of sail area and 20000 kg total mass were assumed
31
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Nuclear Electric Propulsion
Nuclear electric propulsion (NEP) may use ion engines like solar
electric or alternatively magnetohydrodynamic drive It obtains
electricity from a generator heated by a nuclear fission reactor
Thus NEP is not powertlimited by increasing solar distance
Previous studies indicate that an operational SC is possible
by the year 2000 with power levels up to a megawatt (electric) or more
(James et al 1976)
Preliminary estimates were made based on previous calculations for
a Neptune mission Those indicated that heliocentric escape velocity
of 50-60 kms can be obtained
Fusion
With a fusion energy source thermal energy could be converted to
provide ion or MHD drive and charged particles produced by the nuclear
reaction can also be accelerated to produce thrust
A look at one fusion concept gave a V of about 70 kus The
spacecraft weight was 3 x 106 kg Controlled fusion has still to be
attained
Bussard (1960) has suggested that interstellar hydrogen could be
collected by a spacecraft and used to fuel a fusion reaction
Antimatter
Morgan (1975 1976) James et al (1976) and Massier (1977a and b)
have recently examined the use of antimatter-matter annihilation to
obtain rocket thrust A calculation based on Morgans concepts suggests
that a V over 700 Ions could be obtained with a mass comparable to
NEP
Low Thrust Plus Gravity Assist
A possible mix of techniques discussed would be to use a lowshy
thrust propulsion system to target a spacecraft for a Jupiter gravity
assist to achieve a very high V escape If for example one accelerashy
ted a spacecraft to a parabolic orbit as it crossed the orbit of
Jupiter the V at Jupiter would be about 172 kms One could usein
gravity assist then to give a solar system escape V of 24 kus in the
ecliptic plane or inclinations up to about 63 above the plane
Powered swingby at Jupiter could further enhance both V and inclination
32
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A second possibility is to use a solar sail to crank the spaceshy
craft into a retrograde (1800 inclination) orbit and then spiral out to
encounter Jupiter at a V of over 26 kms This would result inan escape V s on the order of 30 kms and inclinations up to 900 thus
covering the entire celestial sphere Again powered swingby would
improve performance but less so because of the high Vin already present
This method is somewhat limited by the decreasing bend angle possible
at Jupiter as Vin increases With still higher approach velocities
the possible performance increment from a Jupiter swingby continues
to decrease
Solar Plus Nuclear Electric
One might combine solar electric with nuclear electric using solar
first and then when the solar distance becomes greater and the solar
distance becomes greater and the solar power falls off switching to NEP
Possibly the same thrusters could be used for both Since operating
lifetime of the nuclear reactor can limit the impulse attainable with NEP
this combination might provide higher V than either solar or nuclear
electric single-stage systems
CHOICE OF PROPULSION
Of the various propulsion techniques outlined above the only
ones that are likely to provide solar system escape velocities above
50 kms utilize either sails or nuclear energy
The sail technique could be used with two basic options solar
sailing going in to perhaps 01 AU from the sun and laser sailing
In either case the requirements on the sail are formidable Figure 3
shows solar sail performance attainable with various spacecraft lightshy
ness factors (ratios of solar radiation force on the SC at normal inshy
cidence to solar gravitational force on the SIC) The sail surface
massarea ratios required to attain various V values are listed in
Table 10 For a year 2000 launch it may be possible to attain a sail
surface massarea of 03 gm2 if the perihelion distance is constrained
to 025 AU or more (W Carroll private communication) This ratio
corresponds to an aluminum film about 100 nm thick which would probably
have to be fabricated in orbit With such a sail a V of about 120 kms
might be obtained
33
77-70
300
Jg 200-
X= 0
U
Ln
Uj LU
jLU
z 100II U 0
01 0 01 02 03
PERIHELION RADIUS AU
Fig 3 Solar System Escape with Ultralight Solar Sails Lightness factor X = (solar radiation force on SC at normal
incidence)(solar gravitational force on SC) From C Uphoff (private communication)
34
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TABLE 10
PERFORMANCE OF ULTRALIGHT SOLAR SAILS
Initial Heliocentric Lightness Sail Sail Perihelion Excess Factor Load Surface Distance Velocity X Efficiency MassArea
Vw aFT1 a F
gm2 gm2 AU kms
025 60 08 20 09
025 100 18 085 04
025 200 55 03 012
01 100 06 27 12
01 200 22 07 03
01 300 50 03 014
Notes
X = (solar radiation force on SC at normal (incidence)(solar gravitational force on SC)
aT = (total SC mass)(sail area)
p = sail efficiency
= includes sail film coatings and seams excludes structuraloF and mechanical elements of sail and non-propulsive portions
of SC Assumed here IF= 05 aT P = 09
Initial orbit assumed semi-major axis = 1 x 108 1cm Sail angle optimized for maximum rate of energy gain
35
77-70
If the perihelion distance is reduced to 01 AU the solar radiashy
tion force increases but so does the temperature the sail must withstand
With a reflectivity of 09 and an emissivity of 10 the sail temperature
would reach 470C (740 K) so high temperature material would have to
be used Further according to Carroll (ibid) it may never be possible
to obtain an emissivity of 10 with a film mass less than 1 gm2
because of the emitted wavelengththickness ratio For such films an
emissivity of 05 is probably attainable this would increase the temperashy
ture to over 6000 C (870 K) Carbon films can be considered but they
would need a smooth highly reflective surface It is doubtful a sail
surface massarea less than 1 gm2 could be obtained for use at 6000 C This sail should permit reaching V of 110 kms no better than for the
025 AU design
For laser sailing higher reflectivity perhaps 099 can be
attained because the monochromatic incident radiation permits effective
use of interference layers (Carroll ibid) Incident energy flux
equivalent to 700 suns (at 1 AU) is proposed however The high
reflectivity coating reduces the absorbed energy to about the level of
that for a solar sail at 01 AU with problems mentioned above Vs up
to 200 kms might be achieved if the necessary very high power lasers
were available in orbit
-Considering nuclear energy systems a single NEP stage using
fission could provide perhaps 60 to 100 kms V NEP systems have
already been the subject of considerable study and some advanced developshy
ment Confidence that the stated performance can be obtained is thereshy
fore higher than for any of the competing modes Using 2 NEP stages or
a solar electric followed by NEP higher V could be obtained one
preliminary calculation for 2 NEP stages (requiring 3 shuttle launches
or the year 2000 equivalent) gave V = 150 kms
The calculation for a fusion propulsion system indicates 30
spacecraft velocity improvement over fission but at the expense of
orders of magnitude heavier vehicle The cost would probably be proshy
hibitive Moreover controlled fusion has not yet been attained and
development of an operational fusion propulsion system for a year 2000
launch is questionable As to collection of hydrogen enroute to refuel
a fusion reactor this is further in the future and serious question
exists as to whether it will ever be feasible (Martin 1972 1973)
An antimatter propulsion system is even more speculative than a
fusion system and certainly would not be expected by 2000 On the other
36
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hand the very rough calculations indicate an order of magnitude velocity
improvement over fission NEP without increasing vehicle mass Also
the propulsion burn time is reduced by an order of magnitude
On the basis of these considerations a fission NEP system was
selected as baseline for the remainder of the study The very lightshy
weight solar sail approach and the high temperature laser sail approach
may also be practical for a year 2000 mission and deserve further
study The antimatter concept is the most far out but promises orders
of magnitude better performance than NEP Thus in future studies
addressed to star missions antimatter propulsion should certainly be
considered and a study of antimatter propulsion per se is also warranted
37
77-70
MISSION CONCEPT
The concept which evolved as outlined above is for a mission outshy
ward to 500-1000 AU directed toward the incoming interstellar gas
Critical science measurements would be made when passing through the
heliopause region and at as great a range as possible thereafter The
location of the heliopause is unknown but is estimated as 50-100 AU
Measurements at Pluto are also desired Launch will be nominally in
the year 2000
The maximum spacecraft lifetime considered reasonable for a year
2000 launch is 50 years (This is discussed further below) To
attain 500-1000 AU in 50 years requires a heliocentric excess velocity
of 50-100 kms The propulsion technique selected as baseline is NEP
using a fission reactor Either 1 or 2 NEP stages may be used If 2 NEP
stages are chosen the first takes the form of an NEP booster stage and the
second is the spacecraft itself The spacecraft with or without an NEP
booster stage is placed in low earth orbit by some descendant of the
Shuttle NEP is then turned on and used for spiral earth escape Use of
boosters with lower exhaust velocity to go to high earth orbit or earth
escape is not economical The spiral out from low earth orbit to earth
escape uses only a small fraction of the total NEP burn time and NEP proshy
pellant
After earth escape thrusting continues in heliocentric orbit A
long burn time is needed to attain the required velocity 5 to 10 years are
desirable for single stage NEP (see below) and more than 10 years if two
NEP stages are used The corresponding burnout distance depending on the
design may be as great as 200 AU or even more Thus propulsion may be on
past Pluto (31 AU from the sun in 2005) and past the heliopause To measure
the mass of Pluto a coasting trajectory is needed thrust would have to be
shut off temporarily during the Pluto encounter The reactor would continue
operating at a low level during the encounter to furnish spacecraft power
Attitude control would preferably be by momentum wheels to avoid any disturshy
bance to the mass measurements Scientific measurements including imagery
would be made during the fast flyby of Pluto
38
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After the Pluto encounter thrusting would resume and continue until
nominal thrust termination (burnout) of the spacecraft Enough propelshy
lant is retained at spacecraft burnout to provide attitude control (unloadshy
ing the momentum wheels) for the 50 year duration of the extended mission
At burnout the reactor power level is reduced and the reactor provides
power for the spacecraft including the ion thrusters used for attitude control
A very useful add-on would be a Pluto Orbiter This daughter spacecraft
would be separated early in the mission at approximately the time solar
escape is achieved Its flight time to Pluto would be about 12 years and its
hyperbolic approach velocity at Pluto about 8 kms
The orbiter would be a full-up daughter spacecraft with enough chemical
propulsion for midcourse approach and orbital injection It would have a
full complement of science instruments (including imaging) and RTG power
sources and would communicate directly to Earth
Because the mass of a dry NEP propulsion system is much greater than
that required for the other spacecraft systems the added mass of a daughter
SC has relatively little effect on the total inert mass and therefore relatively
little effect on propulsive performance The mother NEP spacecraft would fly by
Pluto 3 or 4 years after launch so the flyby data will be obtained at least
5 years before the orbiter reaches Pluto Accordingly the flyby data can be
used in selecting the most suitable orbit for the daughter-spacecraft
If a second spacecraft is to be flown out parallel to the solar axis
it could be like the one going toward the incoming interstellar gas but
obviously would not carry an orbiter Since the desired heliocentric escape
direction is almost perpendicular to the ecliptic somewhat more propulsive
energy will be required than for the SC going upwind if the same escape
velocity is to be obtained A Jupiter swingby may be helpful An NEP booster
stage would be especially advantageous for this mission
39
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MASS DEFINITION AND PROPULSION
The NEP system considered is similar to those discussed by Pawlik and
Phillips (1977) and by Stearns (1977) As a first rule-of-thumb approximation
the dry NEP system should be approximately 30-35 percent of the spacecraft
mass A balance is then required between the net spacecraft and propellant
with mission energy and exhaust velocity being variable For the very high
energy requirements of the extraplanetary mission spacecraft propellant
expenditure of the order of 40-60 percent may be appropriate A booster
stage if required may use a lower propellant fraction perhaps 30 percent
Power and propulsion system mass at 100-140 kms exhaust velocity will
be approximately 17 kgkWe This is based on a 500 kWe system with 20 conshy
version efficiency and ion thrusters Per unit mass may decrease slightly
at higher power levels and higher exhaust velocity Mercury propellant is
desired because of its high liquid density - 136 gcm3 or 13600 kgm3
Mercury is also a very effective gamma shield If an NEP booster is to be
used it is assumed to utilize two 500 We units
The initial mass in low earth orbit (M ) is taken as 32000 kg for
the spacecraft (including propulsion) and as 90000 kg for the spacecraft
plus NEP booster 32000 kg is slightly heavier than the 1977 figure for
the capability of a single shuttle launch The difference is considered
unimportant because 1977 figures for launch capability will be only of
historical interest by 2000 90000kg for the booster plus SC would reshy
quire the year 2000 equivalent of three 1977 Shuttle launches
Figure 4 shows the estimated performance capabilities of the propulsion
system for a single NEP stage
A net spacecraft mass of approximately 1200 kg is assumed and may be broken
out in many ways Communication with Earth is a part of this and may trade off
with on-board automation computation and data processing Support structure for
launch of daughter spacecraft may be needed Adaptive science capability is also
possible The science instruments may be of the order of 200-300 kg (including
a large telescope) and utilize 200 kg of radiation shielding (discussed below)
and in excess of 100 W of power Communications could require as much as 1 kW
40
140 140
120 120
- w
0 u
-J0 a W=
LUlt
HV
70
60
_u
gt
--Ve = 100 Msc = 0
Ve = 120 M = 2000
= 140 Mpsc = 4000 e ~V00 FORZ
= =0x 120 Mpc = 2000
e = Vze = 140 Mpsc = 4000
80
-60
U
lt
z 0
LU
z
U o -J
40
20-
LUn
40
- 20
3
0 0 2 4 6
NET SPACECRAFT
8 10 12
MASS (EXCLUDING PROPULSION)
14
kg x 10 3
16 0
18
Fig 4 Performance of NEP for Solar Escape plus Pluto 17 kgkWe
Ratio (propulsion system dry mass less tankage)(power input to thrust subsystem) =
a= = 32000 kg
M O = initial mass (in low Earth orbit)
Mpsc = mass of a Pluto SC separated when heliocentric escape velocity is attained (kg)
Ve = exhaust velocity (kms)
77-70
One to two kWe of auxiliary power is a first order assumption
The Pluto Orbiter mass is taken as 500 kg plus 1000 kg of chemical
propellant This allows a total AV of approximately 3500 ms and should
permit a good capture orbit at Pluto
The reactor burnup is taken to be the equivalent of 200000 hours at
full power This will require providing reactor control capability beyond
that in existing NEP concepts This could consist of reactivity poison
rods or other elements to be removed as fission products build up together
with automated power system management to allow major improvement in adaptive
control for power and propulsion functions The full power operating time
is however constrained to 70000 h (approximately 8 yr) The remaining
burnup is on reduced power operation for SC power and attitude control
At 13 power this could continue to the 50 yr mission duration
Preliminary mass and performance estimates for the selected system are
given in Table 11 These are for a mission toward the incoming interstellar
wind The Pluto orbiter separated early in the mission makes very little
difference in the overall performance The NEP power level propellant
loading and booster specific impulse were not optimized in these estimates
optimized performance would be somewhat better
According to Table 11 the performance increment due to the NEP booster
is not great Unless an optimized calculation shows a greater increment
use of the booster is probably not worthwhile
For a mission parallel to the solar axis a Jupiter flyby would permit
deflection to the desired 830 angle to the ecliptic with a small loss in VW
(The approach V at Jupiter is estimated to be 23 kms)
in
42
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TABLE 11
Mass and Performance Estimates for Baseline System
(Isp and propellant loading not yet optimized)
Allocation Mass kg
Spacecraft 1200
Pluto orbiter (optional) 1500
NEP (500 kWe) 8500
Propellant Earth spiral 2100
Heliocentric 18100
Tankage 600
Total for 1-stage (Mo earth orbit) 32000
Booster 58000
Total for 2-stage (M earth orbit) 90000
Performance 1 Stage 2 Stages
Booster burnout Distance 8 AU
Hyperbolic velocity 25 kms
Time - 4 yr
Spacecraft burnout Distance (total) 65 155 AU
Hyperbolic velocity 105 150 kms
Time (total) 8 12 yr
Distance in 20 yr 370 410 AU
50 yr 1030 1350 AU
43
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INFORMATION MANAGEMENT
DATA GENERATION
In cruise mode the particles and fields instruments if reading
continuously will generate 1 to 2 kbs of data Engineering sensors
will provide less Spectrometers may provide higher raw data rates
but only occasional spectrometric observations would be needed Star
TV if run at 10 framesday (exposures would probably be several hours)
at 108 bframe would provide about 10 kbs on the average A typical
TV frame might include 10 star images whose intensity need be known
only roughly for identification Fifteen position bits on each axis
and 5 intensity bits would make 350 bframe or 004 bs of useful data
Moreover most of the other scientific quantities mentioned would be
expected to change very slowly so that their information rate will be
considerably lower than their raw data rate Occasional transients
may be encountered and in the region of the heliopause and shock rapid
changes are expected
During Pluto flyby data accumulates rapidly Perhaps 101 bits
mostly TV will be generated These can be played back over a period
of weeks or months If a Pluto orbiter is flown it could generate
1010 bday-or more an average of over 100 kbs
INFORMATION MANAGEMENT SYSTEM
Among the functions of the information handling system will be
storage and processing of the above data The system compresses the data
removing the black sky that will constitute almost all of the raw bits
of the star pictures It will remove the large fraction of bits that
need not be transmitted when a sensor gives a steady or almost-steady
reading It will vary its processing and the output data stream to
accommodate transients during heliopause encounter and other unpredicshy
table periods of high information content
The spacecraft computers system will provide essential support
to the automatic control of the nuclear reactor It will also support
control monitoring and maintenance of the ion thrusters and of the
attitude control system as well as antenna pointing and command processshy
ing
44
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According to James et al (1976)the following performance is proshy
jected for a SC information management system for a year 2000 launch
Processing rate 109 instructions
Data transfer rate -i09 bs
Data storage i014 b
Power consumption 10 - 100 W
Mass -30 kg
This projection is based on current and foreseen state of the art
and ignores the possibility of major breakthroughs Obviously if
reliability requirements can be met the onboard computer can provide
more capability than is required for the mission
The processed data stream provided by the information management
system for transmission to earth is estimated to average 20-40 bs during
cruise Since continuous transmission is not expected (see below) the
output rate during transmission will be higher
At heliosphere encounter the average rate of processed data is
estimated at 1-2 kbs
From a Pluto encounter processed data might be several times 1010
bits If these are returned over a 6-month period the average rate
over these months is about 2 kbs If the data are returned over a
4-day period the average rate is about 100 kbs
OPERATIONS
For a mission lasting 20-50 years with relatively little happenshy
ing most of the time it is unreasonable to expect continuous DSN
coverage For the long periods of cruise perhaps 8 h of coverage per
month or 1 of the time would be reasonable
When encounter with the heliopause is detected it might be possible
to increase the coverage for a while 8 hday would be more than ample
Since the time of heliosphere encounter is unpredictable this possishy
bility would depend on the ability of the DSN to readjust its schedule
quickly in near-real time
For Pluto flyby presumably continuous coverage could be provided
For Pluto orbiters either 8 or 24 hday of coverage could be provided
for some months
45
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DATA TRANSMISSION RATE
On the basis outlined above the cruise data at 1 of the time
would be transmitted at a rate of 2-4 kbs
If heliopause data is merely stored and transmitted the same 1 of
the time the transmission rate rises to 100-200 kbs An alternative
would be to provide more DSN coverage once the heliosphere is found
If 33 coverage can be obtained the rate falls to 3-7 kbs
For Pluto flyby transmitting continuously over a 6-month period
the rate is 2 kbs At this relatively short range a higher rate say
30-100 kbs would probably be more appropriate This would return the
encounter data in 4 days
The Pluto orbiter requires a transmission rate of 30-50 kbs at 24 hday
or 90-150 kbs at 8 hday
TELEMETRY
The new and unique feature of establishing a reliable telecommunicashy
tions link for an extraplanetary mission involves dealing with the
enormous distance between the spacecraft (SC) and the receiving stations
on or near Earth Current planetary missions involve distances between
the SC and receiving stations of tens of astronomical units (AU) at
most Since the extraplanetary mission could extend this distance
to 500 or 1000 AU appropriate extrapolation of the current mission
telecommunication parameters must be made Ideally this extrapolation
should anticipate technological changes that will occur in the next
20-25 years and accordingly incorporate them into the telecommunicashy
tions system design In trying to achieve this ideal we have developed
a baseline design that represents reasonably low risk Other options
which could be utilized around the year 2000 but which may require
technological advancement (eg development of solid state X-band or
Ku-band transmitters) or may depend upon NASAs committing substantial
funds for telemetry link reconfiguration (eg construction of a spaceshy
borne deep space receiver) are examined to determine how they might
affect link capabilities
In the following paragraphs the basic model for the telecommunicashy
tions link is developed Through the range equation transmitted and
received powers are related to wavelength antenna dimensions and
separation between antennas A currently used form of coding is
46
77-70
assumed while some tracking loop considerations are examined A baseline
design is outlined The contributions and effects of various components
to link performance is given in the form of a dB table breakdown
Other options of greater technological or funding risk are treated
Finally we compare capability of the various telemetry options with
requirements for various phases of the mission and identify the teleshy
metry - operations combinations that provide the needed performance
THE TELECOMMUNICATION MODEL
Range Equation
We need to know how much transmitted power is picked up by
the receiving antenna The received power Pr is given approximately by
2 PPr = Ar(R)r i
where
= product of all pertinent efficiencies ie transmitter
power conversion efficiency antenna efficiencies etc
P = power to transmitter
AtA = areas of transmitter receiver antennas respectivelyr
X = wavelength of transmitted radiation
R = range to spacecraft
This received signal is corrupted by noise whose effective power spectral
density will be denoted by NO
Data Coding Considerations
We are assuming a Viterbi (1967) coding scheme with constraint
length K = 7 and rate v = 13 This system has demonstrated quite good
performance producing a bit error rate (BER) of 10- 4 when the informashy
tion bLt SNR is pD - 32 dB (Layland 1970) Of course if more suitable
schemes are developed in the next 20-25 years they should certainly be
used
Tracking Loop Considerations
Because of the low received power levels that can be expected
in this mission some question arises as to whether the communication
47
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system should be coherent or non-coherent The short term stability
of the received carrier frequency and the desired data rate R roughly
determine which system is better From the data coding considerations
we see that
PDIN0 DR 2 RD (2)
where PD is the power allocated to the data Standard phase-locked D 2
loop analysis (Lindsey 1972) gives for the variance a of the phase
error in the loop
2 NO BLPL (3)
where PL is the power allocated to phase determination and BL is the
2closed loop bandwidth (one-sided) In practice a lt 10- 2 for accepshy
table operation so
eL N0 Z 100 BL (4)
The total received power Pr (eq (1) ) is the sum of P L and PD To
minimize PrN subject to the constraint eqs (2) and (4) we see that
a fraction
2D
(5)100 BL + 2
of the received power must go into the data Sincecoherent systems are
3 dB better than non-coherent systems for binary signal detection
(Wozencraft and Jacobs 1965) coherent demodulation is more efficient
whenever
Z 50 BL (6)
48
77-70
Current deep space network (DSN) receivers have BL 110 Hz so for data
rates roughly greater than 500 bitss coherent detection is desirable
However the received carrier frequencies suffer variations from
Doppler rate atmospheric (ionospheric) changes oscillator drifts etc
If received carrier instabilities for the extraplanetary mission are
sufficiently small so that a tracking loop bandwidth of 1 Hz is adeshy
quate then data rates greater than 50 bitss call for coherent
demodulation
These remarks are summarized by the relation between PrIN and
data rate R
2R + 100 BL for R gt 50 BL (coherent system) ) (7) PrINo 4RD for ltlt 50 BL (non-coherent system)
This relation is displayed in Figure 5 where PrIN is plotted vs R for
BL having values 1 Hz and 10 Hz In practice for R gt 50 BL the
approach of PrIN to its asymptotic value of 2 R could be made slightly
faster by techniques employing suppressed carrier tracking loops which
utilize all the received power for both tracking and data demodulation
However for this study these curves are sufficiently accurate to
ascertain Pr IN levels necessary to achieve desired data rates
BASELINE DESIGN
Parameters of the System
For a baseline design we have tried to put together a system
that has a good chance of being operational by the year 2000 Conshy
sequently in certain areas we have not pushed current technology but
have relied on fairly well established systems In other areas we
have extrapolated from present trends but hopefully not beyond developshy
ments that can be accomplished over 20-25 years This baseline design
will be derived in sufficient detail so that the improvement afforded
by the other options discussed in the next section can be more
easily ascertained
First we assume that received carrier frequency stabilities
allow tracking with a loop bandwidth BL 1 Ez This circumstance
is quite likely if an oscillator quite stable in the short term is carried
49
77-70
on the SC if the propulsion systems are not operating during transshy
mission at 1000 AU (Doppler rate essentially zero) and if the receiver
is orbiting Earth (no ionospheric disturbance) Second we assume
data rates RD of at least 100 bitss at 1000 AU or 400 bs at 50 AU
are desired From the discussion preceding eq (6) and Figure 5 we
see this implies a coherent demodulation system with PrN to exceed
25 dB
As a baseline we are assuming an X-band system (X = 355 cm) with
40 watts transmitter power We assume the receiving antenna is on Earth
(if this assumption makes BL 11 Hz unattainable then the value of Pr IN
for the non-coherent system only increases by 1 dB) so the system noise
temperature reflects this accordingly
Decibel Table and Discussion
In Table 12 we give the dB contributions from the various parashy
meters of the range eq (1) loop tracking and data coding By design
the parameters of this table give the narrowest performance margins
If any of the other options of the next section can be realized pershy
formance margin and data rate should correspondingly increase
The two antenna parameters that are assumed require some
explanation A current mission (SEASAT-A) has an imaging radar antenna
that unfurls to a rectangular shape 1075 m x 2 m so a 15 m diameter
spaceborne antenna should pose no difficulty by the year 2000 A 100 m
diameter receiving antenna is assumed Even though the largest DSN
antenna is currently 64 m an antenna and an array both having effecshy
tive area _gt (100 m)2 will be available in West Germany and in this country
in the next five years Consequently a receiver of this collecting
area could be provided for the year 2000
OPTIONS
More Power
The 40 watts transmitter power of the baseline should be
currently realizable being only a factor of 2 above the Voyager value
This might be increased to 05 - 1 kW increasing received signal power
by almost 10-15 dB allowing (after some increase in performance margin)
a tenfold gain in data rate 1 kbs at 1000 AU 4 kbs at 500 AU The
problem of coupling this added energy into the transmission efficiently may
cause some difficulty and should definitely be investigated
50
77-70
70
60-
N
50-
NON-COHERENT
COHERENT BL 10 Hz
0 z
L 30shy
---- BL 10 Hz
20shy
10-
10
0
0
I
10
Fig 5
BL = Hz
CO-COHERENTH
BL =1Hz
I II
20 30 40
DATA RATE RD (dB bitssec) Data Rate vs Ratio of Signal Power to Noise Spectral Power Density
I
50 60
51
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Table 12 BASELINE TELEMETRY AT 1000 AU
No Parameter Nominal Value
1 Total Transmitter power (dBm) (40 watts) 46
2 Efficiency (dB) (electronics and antenna losses) -9
3 Transmitting antenna gain (dB) (diameter = 15 m) 62
4 Space loss (dB) (A47R)2 -334
X = 355 cm R = 1000 AU
5 Receiving antenna gain (dB) (diameter = 100m) 79
6 Total received power (dBm) (P r) -156
7 Receiver noise spectral density (dBmHz) (N0 )
kT with T = 25 K -185
Tracking (if BL = 1 H4z is achievable)
8 Carrier powertotal power 9dB) -5
(100 B L(100BL + 2 R))
9 Carrier power (dBm) (6+ 8) -161
10 Threshold SNR in 2 BL (dB) 20
11 Loop noise bandwidth (dB) (BL) 0
12 Threshold carrier power (dBm) (7 + 10 + 11) -165
13 Performance margin (dB) (9 - 12) 4
Data Channel
14 Estimated loss (waveform distortion bit sync
etc) (B) -2
15 Data powertotal power (dB) -2
(2RD(100BL+ 2RD ) )
16 Data power (dBm) (6 + 14 + 15) -160
17 Threshold data power (dBm) (7 + 17a + 17b) -162
-a Threshold PrTN0 (BER = 10 4 3
b Bit rate (dB BPS) 20
18 Performance margin (dB) (16 - 17) 2
If a non-coherent system must be used each of these values are reduced by
approximately 1 dB
52
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Larger Antennas and Lower Noise Spectral Density
If programs calling for orbiting DSN station are funded then
larger antennas operating at lower noise spectral densitites should beshy
come a reality Because structural problems caused by gravity at the
Earths surface are absent antennas even as large as 300 m in diameter
have been considered Furthermore assuming problems associated with
cryogenic amplifiers in space can be overcome current work indicates
X-band and Ku-band effective noise temperatures as low as 10 K and 14 K
respectively (R C Clauss private communication) These advances
would increase PrN by approximately 12-13 dB making a link at data
rates of 2 kbs at 1000 AU and 8 kbs at 500 AU possible
Higher Frequencies
Frequencies in the Ku-band could represent a gain in directed
power of 5-10 dB over the X-band baseline but probably would exhibit
noise temperatures 1-2 dB worse (Clauss ibid) for orbiting receivers
Also the efficiency of a Ku-band system would probably be somewhat less
than that of X-band Without further study it is not apparent that
dramatic gains could be realized with a Ku-band system
Frequencies in the optical or infrared potentially offer treshy
mendous gains in directed power However the efficiency in coupling
the raw power into transmission is not very high the noise spectral
density is much higher than that of X-band and the sizes of practical
antennas are much smaller than those for microwave frequencies To
present these factors more quantitatively Table 13 gives parameter conshy
tributions to Pr and N We have drawn heavily on Potter et al (1969) and
on M S Shumate and R T Menzies (private communication) to compile
this table We assume an orbiting receiver to eliminate atmospheric
transmission losses Also we assume demodulation of the optical signal
can be accomplished as efficiently as the microwave signal (which is
not likely without some development) Even with these assumptions
PrN for the optical system is about 8 dB worse than that for X-band
with a ground receiver
Pointing problems also become much more severe for the highly
directed optical infrared systems Laser radiation at wavelength 10 Pm
6from a 1 m antenna must be pointed to 5 x 10- radians accuracy
The corresponding pointing accuracy of the baseline system is 10- 3 radians
53
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Table 13 OPTICAL TELEMETRY AT 1000 AU
Nominal ValueParameterNo
461 Total Transmitter power (dBm) (40 watts)
2 Efficiency (dB) (optical pumping antenna losses -16
and quantum detection)
3 Transmitting antenna gain (dB) (diameter = 1 m) 110
Space loss (dB) (A4r) 2 4
X =lO pm r =1000 AU -405
5 Receiving antenna gain (dB) (diameter = 3m) 119
6 Total Received power (dBm) (P ) -146
7
-
Receiver noise spectral density (dBmHz) (N0) -167
(2 x 10 2 0 wattHZ)
54
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Higher Data Rates
This mission may have to accommodate video images from Pluto
The Earth-Pluto separation at the time of the mission will be about 31
AU The baseline system at 31 AU could handle approximately 105 bs
For rates in excess of this one of the other option enhancements would
be necessary
SELECTION OF TELEMETRY OPTION
Table 14 collects the performance capabilities of the various
telemetry options Table 15 shows the proposed data rates in various
SC systems for the different phases of the mission In both tables 2
the last column lists the product (data rate) x (range) as an index
of the telemetry capability or requirements
Looking first at the last column of Table 15 it is apparent that
the limiting requirement is transmittal of heliopause data if DSN
coverage can be provided only 1 of the time If DSN scheduling is
sufficiently flexible that 33 coverage can be cranked up within a
month or so after the heliosphere is detected then the limiting
requirement is transmittal of cruise data (at 1 DSN coverage) For
these two limiting cases the product (data rate) x (range)2 is respecshy8 8 2
tively2-40 x 10 and 5-10 x 10 (bs) AU
Looking now at the last column of Table 14 to cover the cruise
requirement some enhancement over the baseline option will be needed
Either increasing transmitter power to 05-1 kW or going to orbiting DSN
stations will be adequate No real difficulty is seen in providing the
increased transmitter power if the orbiting DSN is not available
If however DSN coverage for transmittal of recorded data from
the unpredictable heliosphere encounter is constrained to 1 of the
time (8 hmonth) then an orbital DSN station (300-m antenna) will be
needed for this phase of the mission as well as either increased transshy
mitter power or use of K-band
55
TABLE 14
TELEMETRY OPTIONS
(Data Rate) Data Rate (bs) x (Range)
Improvement OPTIONS Over Baseline
dB At
1000 AU At
500 AU At
150 AU At 31 AU (bs) bull AU2
Baseline (40 W 100-m receiving antenna X-band) ---- 1 x 102 4 x 102 4 x 103 1 x 105 1 x 108
More power (05 shy 1 kW) 10-15 1 x 103 4 x 103 4 x 104 1 x 106 1 x 109
Orbiting DSN (300-m antenna) X-band (10 K noise temperature) 13 2 x 103 9 x 104 2 x 106 2 x 109
K-band (14 K noise temperature) 17 5 x 103 2 x 10 2 x 10 5 x 10 5 x 109 C)
Both more power and orbiting DSN
X-band 23-28 3 x 104 12 x 105 1 x 106 3 x 107 3 x 1010
TABLE 15
PROPOSED DATA RATES
Tele-Communi- Estimated Data Rate bs (Data
cation Processed Fraction tate Misslon Range Raw Data Transmitted of Time x (Range)2
Phase AU Data Average Data Transmitting bs Au2
Cruise 500 I 12-15 x 104 2-4 x 101 2-4 x 103 001 5-10 x 108
Heliopause 50- 112-15 x 10 31-2
1-2 x 103 x 105 001 2-40 x 108
150 033 08-15 x 107
l SI5 x 105 033 1 x 108
Pluto Flyby -31 1-2 x 10 3-5 x 104
1 11 (10 total
I bits)
10 (3 x 10 bits)
3x10100 x 10
3 x10
15 4 9-15 x 104 033 9-15 x 107
Pluto Orbiter -31 11-2 x 10 3-5 x 104 3-5 x10 4 100 3-5 x 0
To return flyby data in 4 days
77-70
RELATION OF THE MISSION TO
SEARCH FOR EXTRATERRESTRIAL INTELLIGENCE
The relation of this mission to the search for extraterrestrial
intelligence appears to lie only in its role in development and test
of technology for subsequent interstellar missions
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TECHNOLOGY REQUIREMENTS AND PROBLEM AREAS
LIFETIME
A problem area common to all SC systems for this mission is that of
lifetime The design lifetime of many items of spacecraft equipment is now
approaching 7 years To increase this lifetime to 50 years will be a very
difficult engineering task
These consequences follow
a) It is proposed that the design lifetime of the SC for this mission
be limited to 20 years with an extended mission contemplated to a total of
50 years
b) Quality control and reliability methods such as failure mode effects
and criticality analysis must be detailed and applied to the elements that
may eventually be used in the spacecraft so as to predict what the failure
profile will be for system operating times that are much longer than the test
time and extend out to 50 years One approach is to prepare for design and
fabrication from highly controlled materials whose failure modes are
completely understood
c) To the extent that environmental or functional stresses are conceived
to cause material migration or failure during a 50-year period modeling and
accelerated testing of such modes will be needed to verify the 50-year scale
Even the accelerated tests may require periods of many years
d) A major engineering effort will be needed to develop devices circuits
components and fabrication techniques which with appropriate design testing
and quality assurance methods will assure the lifetime needed
PROPULSION AND POWER
The greatest need for subsystem development is clearly in propulsion
Further advance development of NEP is required Designs are needed to permit
higher uranium loadings and higher burnup This in turn will require better
control systems to handle the increased reactivity including perhaps throw-away
control rods Redundancy must be increased to assure long life and moving
parts will need especial attention Development should also be aimed at reducing
system size and mass improving efficiency and providing better and simpler
thermal control and heat dissipation Simpler and lighter power conditioning
59
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is needed as are ion thrusters with longer lifetime or self-repair capability
Among the alternatives to fission NEP ultralight solar sails and laser
sailing look most promising A study should be undertaken of the feasibility
of developing ultra-ltght solar sails (sails sufficiently light so that the
solar radiation pressure on the sail and spacecraft system would be greater
than the solar gravitational pull) and of the implications such development
would have for spacecraft design and mission planning Similarly a study
should be made of the possibility of developing a high power orbiting laser
system together with high temperature spacecraft sails and of the outer planet
and extraplanetary missions that could be carried out with such laser sails
Looking toward applications further in the future an antimatter propulshy
sion system appears an exceptionally promising candidate for interstellar
missions and would be extremely useful for missions within the solar system
This should not be dismissed as merely blue sky matter-antimatter reactions
are routinely carried out in particle physics laboratories The engineering
difficulties of obtaining an antimatter propulsion system will be great conshy
taining the antimatter and producing it in quantity will obviously be problems
A study of possible approaches would be worthwhile (Chapline (1976) has suggested
that antimatter could be produced in quantity by the interaction of beams of
heavy ions with deuteriumtritium in a fusion reactor) Besides this a more
general study of propulsion possibilities for interstellar flight (see Appendix
C) should also be considered
PROPULSIONSCIENCE INTERFACE
Three kinds of interactions between the propulsionattitude control
system and science measurements deserve attention They are
1) Interaction of thrust and attitude control with mass measurements
2) Interaction of electrical and magnetic fields primarily from the
thrust subsystem with particles and fields measurements
3) Interactions of nuclear radiation primarily from the power subsystem
with photon measurements
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Interaction of thrust with mass measurements
It is desired to measure the mass of Pluto and of the solar system as
a whole through radio tracking observations of the spacecraft accelerations
In practice this requires that thrust be off during the acceleration obsershy
vations
The requirement can be met by temporarily shutting off propulsive
thrusting during the Pluto encounter and if desired at intervals later on
Since imbalance in attitude control thrusting can also affect the trajectory
attitude control during these periods should preferably be by momentum wheels
The wheels can afterwards be unloaded by attitude-control ion thrusters
Interaction of thrust subsystem with particles and fields measurements
A variety of electrical and magnetic interference with particles and fields
measurements can be generated by the thrust subsystem The power subsystem can
also generate some electrical and magnetic interference Furthermore materials
evolved from the thrusters can possibly deposit upon critical surfaces
Thruster interferences have been examined by Sellen (1973) by Parker et al
(1973) and by others It appears that thruster interferences should be reducshy
ible to acceptable levels by proper design but some advanced development will
be needed Power system interferences are probably simpler to handle Essenshy
tially all the thruster effects disappear when the engines are turned off
Interaction of power subsystem with photon measurements
Neutrons and gamma rays produced by the reactor can interfere with
photon measurements A reactor that has operated for some time will be highly
radioactive even after it is shut down Also exposure to neutrons from the
reactor will induce radioactivity in other parts of the spacecraft In the
suggested science payload the instruments most sensitive to reactor radiation
are the gamma-ray instruments and to a lesser degree the ultraviolet
spectrometer
A very preliminary analysis of reactor interferences has been done
Direct neutron and gamma radiation from the reactor was considered and also
neutron-gamma interactions The latter were found to be of little significance if
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the direct radiation is properly handled Long-lived radioactivity is no problem
except possibly for structure or equipment that uses nickel Expected
flux levels per gram of nickel are approximately 0007 ycm2-s
The nuclear reactor design includes neutron and gamma shadow shielding
to fully protect electronic equipment from radiation damage Requirements
are defined in terms of total integrated dose Neutron dose is to be limited
to 1012 nvt and gamma dose to 106 rad A primary mission time of 20 years is
assumed yielding a LiH neutron shield thickness of 09 m and a mercury gamma
shield thickness of 275 cm (or 2 cm of tungsten) Mass of this shielding is
included in the 8500 kg estimate for the propulsion system
For the science instruments it is the flux that is important not total
dose The reactor shadow shield limits the flux level to 16 x 103 neutrons
or gammascm22 This is apparently satisfactory for all science sensors except
the gamma-ray detectors They require that flux levels be reduced to 10 neutrons22
cm -s and 01 gammacm -s Such reduction is most economically accomplished by local
shielding The gamma ray transient detector should have a shielded area of
2possibly 1200 cm (48 cm x 25 cm) Its shielding will include a tungsten
thickness of 87 cm and a lithium-hydride thickness of 33 cm The weight of
this shielding is approximately 235 kg and is included in the spacecraft mass
estimate It may also be noted that the gamma ray transient detector is probshy
ably the lowest-priority science instrument An alternative to shielding it
would be to omit this instrument from the payload (The gamma ray spectrometer
is proposed as an orbiter instrument and need not operate until the orbiter is
separated from the NEP mother spacecraft) A detailed Monte Carlo analysis
and shield development program will be needed to assure a satisfactory solution
of spacecraft interfaces
TELECOMMUNICATIONS
Microwave vs Optical Telemetry Systems
Eight years ago JPL made a study of weather-dependent data links in
which performance at six wavelengths ranging from S-band to the visible was
analyzed (Potter et al 1969) A similar study for an orbiting DSN (weathershy
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independent) should determine which wavelengths are the most advantageous
The work of this report indicates X-band or K-band are prime candidates but
a more thorough effort is required that investigates such areas as feasibility
of constructing large spaceborne optical antennas efficiency of power convershy
sion feasibility of implementing requisite pointing control and overall costs
Space Cryogenics
We have assumed cryogenic amplifiers for orbiting DSN stations in order
to reach 4-5 K amplifier noise contributions Work is being done that indicates
such performance levels are attainable (R C Clauss private communication
D A Bathker private communication) and certainly should be continued At
the least future studies for this mission should maintain awareness of this
work and probably should sponsor some of it
Lifetime of Telecommunications Components
The telecommunications component most obviously vulnerable to extended
use is the microwave transmitter Current traveling-wave-tube (TWT) assemblies
have demonstrated 11-12 year operating lifetimes (H K Detweiler private
communication also James et al 1976) and perhaps their performance over
20-50 year intervals could be simulated However the simple expedient
measure of carrying 4-5 replaceable TWTs on the missions might pose a
problem since shelf-lifetimes (primarily limited by outgasing) are not known
as well as the operating lifetimes A more attractive solution is use of
solid-state transmitters Projections indicate that by 1985 to 1990 power
transistors for X-band and Ku-band will deliver 5-10 wattsdevice and a few
wattsdevice respectively with lifetimes of 50-100 years (J T Boreham
private communication) Furthermore with array feed techniques 30-100
elements qould be combined in a near-field Cassegrainian reflector for
signal transmission (Boreham ibid) This means a Ku-band system could
probably operate at a power level of 50-200 watts and an X-band system
could likely utilize 02 - 1 kW
Other solid state device components with suitable modular replacement
strategies should endure a 50 year mission
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Baseline Enhancement vs Non-Coherent Communication System
The coherent detection system proposed requires stable phase reference
tracking with a closed loop bandwidth of approximately 1 Hz Of immediate
concern is whether tracking with this loop bandwidth will be stable Moreover
if the tracking is not stable what work is necessary to implement a non-coherent
detection system
The most obvious factors affecting phase stability are the accelerations
of the SIC the local oscillator on the SC and the medium between transmitter
and receiver If the propulsion system is not operating during transmission
the first factor should be negligible However the feasibility of putting on
board a very stable (short term) local oscillator with a 20-50 year lifetime
needs to be studied Also the effect of the Earths atmosphere and the
Planetary or extraplanetary media on received carrier stability must be
determined
If stability cannot be maintained then trade-off studies must be
performed between providing enhancements to increase PrIN and employing
non-coherent communication systems
INFORMATION SYSTEMS
Continued development of the on-board information system capability
will be necessary to support control of the reactor thrusters and other
portions of the propulsion system to handle the high rates of data acquishy
sition of a fast Pluto flyby to perform on-board data filtering and compresshy
sion etc Continued rapid development of information system capability to
very high levels is assumed as mentioned above and this is not considered
to be a problem
THERMAL CONTROL
The new thermal control technology requirement for a mission beyond the
solar system launched about 2000 AD involve significant advancements in thershy
mal isolation techniques in heat transfer capability and in lifetime extension
Extraplanetary space is a natural cryogenic region (_3 K) Advantage may be taken
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of it for passive cooling of detectors in scientific instruments and also
for the operation of cryogenic computers If cryogenic computer systems
and instruments can be developed the gains in reliability lifetime and
performance can be considered However a higher degree of isolation will
be required to keep certain components (electronics fluids) warm in extrashy
planetary space and to protect the cryogenic experiments after launch near
Earth This latter is especially true if any early near-solar swingby is
used to assist escape in the mission A navigational interest in a 01 AU
solar swingby would mean a solar input of 100 suns which is beyond any
anticipated nearterm capability
More efficient heat transfer capability from warm sources (eg RTGs)
to electronicssuch as advanced heat pipes or active fluid loops will be
necessary along with long life (20-50 years) The early mission phase also
will require high heat rejection capability especially for the cryogenic
experiments andor a near solar swingby
NEP imposes new technology requirements such as long-term active heat
rejection (heat pipes noncontaminated radiators) and thermal isolation
NEP also might be used as a heat source for the SC electronics
Beyond this the possibility of an all-cryogenic spacecraft has been
suggested by Whitney and Mason (see Appendix C) This may be more approshy
priate to missions after 2000 but warrants study Again there would be a
transition necessary from Earth environment (one g plus launch near solar)
to extraplanetary environment (zero g cryogenic) The extremely low power
(-1 W)requirement for superconducting electronics and the possibility of
further miniaturation of the SC (or packing in more electronics with low
heat dissipation requirements) is very attractive Also looking ahead the
antimatter propulsion system mentioned above would require cryogenic storage
of both solid hydrogen and solid antihydrogen using superconducting (cryo)
magnets and electrostatic suspension
Table 16 summarizes the unusual thermal control features of an extrashy
planetary mission
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TABLE 16
T-HERMAL CONTROL CHARACTERISTICS OF EXTRAPLANETARY MISSIONS
Baseline Mission
1 Natural environment will be cryogenic
a) Good for cryogenic experiments - can use passive thermal control b) Need for transitien from near Earth environment to extraplanetary
space bull i Can equipment take slow cooling
ii Well insolated near sunt iii Cryogenic control needed near Eartht
2 NEP
a) Active thermal control - heat pipes - lifetime problems b) Heat source has advantages amp disadvantages for SC design
Not Part of Baseline Mission
3 Radioisotope thermal electric generator (RTG) power source provides hot environment to cold SC
a) Requires high isolation b) Could be used as source of heat for warm SC
i Fluid loop - active devices will wear - lifetime problem
ii Heat pipes c) Must provide means of cooling RTGs
4 Close Solar Swingby - 01 AU
a) 100 suns is very high thermal input - must isolate better b) Contrasts with later extraplanetary environment almost no sun c) Solar Sail requirements 03 AU (11 suns) Super Sail 01 AU
Significant technology advancement required
Not part of baseline mission
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COMPONENTS AND MATERIALS
By far the most important problem in this area is prediction of long-term
materials properties from short-term tests This task encompasses most of the
other problems noted Sufficient time does not exist to generate the required
material properties in real time However if in the time remaining we can
establish the scaling parameters the required data could be generated in a
few years Hence development of suitable techniques should be initiated
Another critical problem is obtaining bearings and other moving parts with
50 years lifetime Effort on this should be started
Less critical but also desirable are electronic devices that are inherently
radiation-resistant and have high life expectancy DOE has an effort undershy
way on this looking both at semiconductor devices utilizing amorphous semishy
conductors and other approaches that do not depend on minority carriers and
at non-semiconductor devices such as integrated thermonic circuits
Other special requirements are listed in Table 17
SCIENCE INSTRUMENTS
Both the problem of radiation compatibility of science instruments with NEP
propulsion and the problem of attaining 50-year lifetime have been noted above
Many of the proposed instruments have sensors whose lifetime for even current
missions is of concern and whose performance for this mission is at best uncershy
tain Instruments in this category such as the spectrometers and radiometers
should have additional detector work performed to insure reasorvable-performance
Calibration of scientific instruments will be very difficult for a 20-50 year
mission Even relatively short term missions like Viking and Voyager pose
serious problems in the area of instrument stability and calibration verificashy
tion Assuming that reliable 50-year instruments could be built some means
of verifying the various instrument transfer functions are needed Calibration
is probably the most serious problem for making quantitative measurements on a
50-year mission
The major problems in the development of individual science instruments
are listed below These are problems beyond those likely to be encountered
and resolved in the normal course of development between now and say 1995
or 2000
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77-70 TABLE 17
TECHNOLOGY REQUIREMENTS FOR COMPONENTS amp MATERIALS
1 Diffusion Phenomena 11 Fuses 12 Heaters 13 Thrusters 14 Plume Shields 15 RTGs 16 Shunt Radiator
2 Sublimation and Erosion Phenomena 21 Fuses shy22 Heater 23 Thrusters 24 Plume Shields 25 RTGs 26 Polymers 27 Temperature Control Coatings 28 Shunt Radiator
3 Radiation Effects 31 Electronic components 32 Polymers 33 Temperature Control Coatings 34 NEP and RTG Degradation
4 Materials Compatibility 41 Thrusters 42 Heat Pipes 43 Polymeric Diaphragms amp Bladders 44 Propulsion Feed System
5 Wear and Lubrication 55 Bearings
6 Hermetic Sealing and Leak Testing 61 Permeation Rates 62 Pressure Vessels
7 Long-Term Material Property Prediction from Short-Term Tests 71 Diffusion 72 Sublimation 73 Wear and Lubrication 74 Radiation Effects 75 Compatibility 76 Thermal Effects
8 Size Scale-Up 81 Antennae 82 Shunt Radiator 83 Pressure Vessels
9 Thermal Effects on Material Properties 91 Strength 92 Creep and Stress Rupture
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Neutral Gas Mass Spectrometer
Designing a mass spectrometer to measure the concentration of light gas
species in the interstellar medium poses difficult questions of sensitivity
Current estimates of H concentration in the interstellar medium near the
solar system are 10 --10 atomcm and of He contraction about 10 atomcm
(Bertaux and Blamont 1971 Thomas and Krassna 1974 Weller and Meier 1974
Freeman et al 1977 R Carlson private communication Fahr et al 1977
Ajello 1977 Thomas 1978) On the basis of current estimates of cosmic
relative abundances the corresponding concentration of C N 0 is 10 to
- 410 atomcm3 and of Li Be B about 10-10 atomcm3
These concentrations are a long way beyond mass spectrometer present
capabilities and it is not clear that adequate capabilities can be attained
2by 2000 Even measuring H and He at 10- to H- 1 atomcm 3 will require a conshy
siderable development effort Included in the effort should be
a) Collection Means of collecting incoming gas over a substantial
frontal area and possibly of storing it to increase the input rate
and so the SN ratio during each period of analysis
b) Source Development of ionization sources of high efficiency
and satisfying the other requirements
c) Lifetime Attaining a 50-year lifetime will be a major problem
especially for the source
d) SN Attaining a satisfactory SN ratio will be a difficult
problem in design of the whole instrument
Thus if a mass spectrometer suitable for the mission is to be provided
considerable advanced development work-will be needed
Camera Field of View vs Resolution
Stellar parallax measurements present a problem in camera design because
of the limited number of pixelsframe in conventional and planned spacecraft
cameras For example one would like to utilize the diffraction-limited resoshy
lution of the objective For a 1-m objective this is 012 To find the
center of the circle of confusion accurately one would like about 6 measureshy
ments across it or for a 1-m objective a pizel size of about 002 or 01 vrad
(Note that this also implies fine-pointing stability similar to that for earthshy
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orbiting telescopes) But according to James et al (1976) the number of
elements per frame expected in solid state cameras by the year 2000 is 106
for a single chip and 107 for a mosaic With 107 elements or 3000 x 3000
the field of view for the case mentioned would be 30O0 x 002 = 1 minute of
arc At least five or six stars need to be in the field for a parallax
measurement Thus a density of 5 stars per square minute or 18000 stars
per square degree is needed To obtain this probably requires detecting
stars to about magnitude 26 near the galactic poles and to magnitude 23
near galactic latitude 45 This would be very difficult with a 1-m telescope
A number of approaches could be considered among them
a) Limit parallax observations to those portions of the sky having
high local stellar densities
b) Use film
c) Find and develop some other technique for providing for more
pixels per frame than CCDs and vidicons
d) Sense the total irradiation over the field and develop a masking
technique to detect relative star positions An example would be
the method proposed for the Space Telescope Astrometric Multiplexing
Area Scanner (Wissinger and McCarthy 1976)
e) Use individual highly accurate single-star sensors like the Fine
Guiding Sensors to be used in Space Telescope astrometry (Wissinger
1976)
Other possibilities doubtless exist A study will be needed to determine
which approaches are most promising and development effort may be needed to
bring them to the stage needed for project initiation
The problems of imaging Pluto it may be noted are rather different than
those of star imagery For a fast flyby the very low light intensity at Pluto
plus the high angular rate make a smear a problem Different optical trains
may be needed for stellar parallax for which resolution must be emphasized
and for Pluto flyby for which image brightness will be critical Besides this
image motion compensation may be necessary at Pluto it may be possible to provide
this electronically with CCDs It is expected that these needs can be met by
the normal process of development between now and 1995
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ACKNOWLEDGEMENT
Participants in this study are listed in Appendix A contributors to
the science objectives and requirements in Appendix B Brooks Morris supplied
valuable comments on quality assurance and reliability
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REFERENCES
0 0 J M Ajello (1977) An interpretation of Mariner 10 He (584 A) and H (1216 A)
interplanetary emission observations submitted to Astrophysical Journal
J L Bertaux and J E Blamont (1971) Evidence for a source of an extrashyterrestrial hydrogen Lyman Alpha emission Astron and Astrophys 11 200-217
R W Bussard (1960) Galactic matter and interstellar flight Astronautica Acta 6 179-194
G Chapline (1976) Antimatter breeders Preprint UCRL-78319 Lawrence Livermore Laboratory Livermore CA
H J Fahr G Lay and C Wulf-Mathies (1977) Derivation of interstellar hydrogen parameters from an EUV rocket observation Preprint COSPAR
R L Forward (1962) Pluto - the gateway to the stars Missiles and Rockets 10 26-28
R L Forward (1975) Advanced propulsion concepts study Comparative study of solar electric propulsion and laser electric propulsion Hughes Aircraft Co D3020 Final Report to Jet Propulsion Laboratory JPL Contract 954085
R L Forward (1976) A programme for interstellar exploration Jour British Interplanetary Society 29 611-632
J Freeman F Paresce S Bowyer M Lampton R Stern and B Margon (1977) The local interstellar helium density Astrophys Jour 215 L83-L86
R L Garwin (1958) Solar sailing - A practical method of propulsion within the solar system Jet Propulsion 28 188-190
J N James R R McDonald A R Hibbs W M Whitney R J Mackin Jr A J Spear D F Dipprey H P Davis L D Runkle J Maserjian R A Boundy K M Dawson N R Haynes and D W Lewis (1976) A Forecast of Space Technology 1980-2000 SP-387 NASA Washington DC Also Outlook for Space 1980-2000 A Forecast of Space Technology JPL Doc 1060-42
J W Layland (1970) JPL Space Programs Summary 37-64 II 41
W C Lindsey (1972) Synchronization Systems in Communication and Control Prentice-Hall Englewood Cliffs N J
E F Mallove R L Forward and Z Paprotney (1977) Bibliography of interstellar travel and communication - April 1977 update Hughes Aircraft Co Research Rt 512 Malibu California
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A R Martin (1972) Some limitations of the interstellar ramjet Spaceshyflight 14 21-25
A R Martin (1973) Magnetic intake limitations on interstellar ramjets Astronautics Acta 18 1-10
G Marx (1966) Interstellar vehicle propelled by terrestrial laser beam Nature 211 22-23
P F Massier (1977a) Basic research in advanced energy processes in JPL Publ 77-5 56-57
P F Massier (1977b) Matter-Antimatter Symposium on New Horizons in Propulsion JPL Pasadena California
W E Moeckel (1972) Propulsion by impinging laser beams Jour Spaceshycraft and Rockets 9 942-944
D L Morgan Jr (1975) Rocket thrust from antimatter-matter annihilashytion A preliminary study Contractor report CC-571769 to JPL
D L Morgan (1976) Coupling of annihilation energy to a high momentum exhaust in a matter-antimatter annihilation rocket Contractor report to JPL PO JS-651111
D D Papailiou E J Roschke A A Vetter J S Zmuidzinas T M Hsieh and D F Dipprey (1975) Frontiers in propulsion research Laser matter-antimatter excited helium energy exchange thermoshynuclear fusion JPL Tech Memo 33-722
R H Parker J M Ajello A Bratenahl D R Clay and B Tsurutani (1973) A study of the compatibility of science instruments with the Solar Electric Propulsion Space Vehicle JPL Technical Memo 33-641
E V Pawlik and W M Phillips (1977) Anuclear electric propulsion vehicle for planetary exploration Jour Spacecraft and Rockets 14 518-525
P D Potter M S Shumate C T Stelzried and W H Wells (1969) A study of weather-dependent data links for deep-space applications JPL Tech Report 32-1392
J D G Rather G W Zeiders and R K Vogelsang (1976) Laser Driven Light Sails -- An Examination of the Possibilities for Interstellar Probes and Other Missions W J Schafer Associates Rpt WJSA-76-26 to JPL JPL PD EF-644778 Redondo Beach CA
J M Sellen Jr (1973) Electric propulsion interactive effects with spacecraftscience payloads AIAA Paper 73-559
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A B Sergeyevsky (1971) Early solar system escape missions - An epilogue to the grand tours AAS Preprint 71-383 Presented to AASAIAA Astroshydynamics Specialist Conference
D F Spencer and L D Jaffe (1962) Feasibility of interstellar travel Astronautica Acta 9 49-58
J W Stearns (1977) Nuclear electric power systems Mission applications and technology comparisons JPL Document 760-176 (internal document)
G E Thomas and R F Krassna (1974) OGO-5 measurements of the Lyman Alpha sky background in 1970 and 1971 Astron and Astrophysics 30 223-232
G E Thomas (1978) The interstellar wind and its influence on the interplanetary environment accepted for publication Annual Reviews of Earth and Planetary Science
A J Viterbi (1967) Error bounds for convolutional codes and an asympshytotically optimum decoding algorithm IEEE Transactions on Information Theory IT-3 260
C S Weller and R R Meier (1974) Observations of helium in the intershyplanetaryinterstellar wind The solar-wake effect Astrophysical Jour 193 471-476
A B Wissinger (1976) Space Telescope Phase B Definition Study Final Report Vol II-B Optical Telescope Assembly Part 4 Fine Guidance Sensor Perkin Elmer Corp Report ER-315 to NASA Marshall Space Flight Center
A B Wissinger and D J McCarthy (1976) Space Telescope Phase B Definishytion Study Final Report Vol II-A Science Instruments Astrometer Perkin Elmer Corp Report ER-320(A) to NASA Marshall Space Flight Center
J M Wozencraft and I M Jacobs (1965) Principles of Communication Engineering Wiley New York
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APPENDIX A
STUDY PARTICIPANTS
Participants in this study and their technical areas were as follows
Systems
Paul Weissman
Harry N Norton
Space Sciences
Leonard D Jaffe (Study Leader)
Telecommunications
Richard Lipes
Control amp Energy Conversion
Jack W Stearns
Dennis Fitzgerald William C Estabrook
Applied Mechanics
Leonard D Stimpson Joseph C Lewis Robert A Boundy Charles H Savage
Information Systems
Charles V Ivie
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APPENDIX B
SCIENCE CONTRIBUTORS
The following individuals contributed to the formulation of scientific
objectives requirements and instrument needs during the course of this
study
Jay Bergstrahl Robert Carlson Marshall Cohen (Caltech) Richard W Davies Frank Estabrook Fraser P Fanale Bruce A Goldberg Richard M Goldstein Samuel Gulkis John Huchra (SAO)
Wesley Huntress Jr Charles V Ivie Allan Jacobson Leonard D Jaffe Walter Jaffe (NRAO) Torrence V Johnson Thomas B H Kuiper Raymond A Lyttleton (Cambridge University) Robert J Mackin Michael C Malin Dennis L Matson William G Melbourne Albert E Metzger Alan Moffett (Caltech) Marcia M Neugebauer Ray L Newburn Richard H Parker Roger J Phillips Guenter Riegler R Stephen Saunders Edward J Smith Conway W Snyder Bruce Tsurutani Glenn J Veeder Hugo Wahlquist Paul R Weissman Jerome L Wright
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APPENDIX C
THOUGHTS FOR A STAR MISSION STUDY
The primary problem in a mission to another star is still propulsion
obtaining enough velocity to bring the mission duration down enough to be
of much interest The heliocentric escape velocity of about 100 kms
believed feasible for a year 2000 launch as described in this study is
too low by two orders of magnitude
PROPULSION
A most interesting approach discussed recently in Papailou in James
et al (1976) and by Morgan (1975 1976) is an antimatter propulsion system
The antimatter is solid (frozen antihydrogen) suspended electrostatically
or electromagnetically Antimatter is today produced in small quantities
in particle physics laboratories Chapline (1976) has suggested that much
larger quantities could be produced in fusion reactors utilizing heavy-ion
beams For spacecraft propulsion antimatter-matter reactions have the great
advantage over fission and fusion that no critical mass temperature or reacshy
tion containment time is required the propellants react spontaneously (They
are hypergolic) To store the antimatter (antihydrogen) it would be frozen
and suspended electrostatically or electromagnetically Attainable velocities
are estimated at least an order of magnitude greater than for fission NEP
Spencer and Jaffe (1962) showed that multistage fission or fusion systems
can theoretically attain a good fraction of the speed of light To do this
the products of the nuclear reaction should be used as the propellants and
the burnup fraction must be high The latter requirement may imply that
fuel reprocessing must be done aboard the vehicle
The mass of fusion propulsion systems according to James et al (1976)
is expected to be much greater than that of fission systems As this study
shows the spacecraft velocity attainable with fusion for moderate payloads
is likely to be only a little greater than for fission
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CRYOGENIC SPACECRAFT
P V Mason (private communication 1975) has discussed the advantages
for extraplanetary or interstellar flight of a cryogenic spacecraft The
following is extracted from his memorandum
If one is to justify the cost of providing a cryogenic environment one must perform a number of functions The logical extension of this is to do all functions cryogenically Recently William Whitney suggested that an ideal mission for such a spacecraft would be an ultraplanetary or interstellar voyager Since the background of space is at about 3 Kelvin the spacecraft would approach this temperature at great distances from the Sun using only passive radiation (this assumes that heat sources aboard are kept at a very low level) Therefore I suggest that we make the most optimistic assumptions about low temperature phenomena in the year 2000 and try to come up with a spacecraft which will be far out in design as well as in mission Make the following assumptions
1 The mission objective will be to make measurements in ultraplanetary space for a period of 10 years
2 The spacecraft can be kept at a temperature not greater than 20 Kelvin merely by passive radiation
3 Superconductors with critical temperatures above 20 Kelvin will be available All known superconducting phenomena will be exhibited by these superconductors (eg persistent current Josephson effect quantization of flux etc)
4 All functions aboard the spacecraft are to be performed at 20 Kelvin or below
I have been able to think of the following functions
I SENSING
A Magnetic Field
Magnetic fields in interstellar space are estimated to be about 10-6 Gauss The Josephson-Junction magnetometer will be ideal for measuring the absolute value and fluctuations in this field
B High Energy Particles
Superconducting thin films have been used as alpha-particle detectors We assume that by 2000 AD superconducting devices will be able to measure a wide variety of energetic particles Superconducting magnets will be used to analyze particle energies
C Microwave and Infrared Radiation
It is probable that by 2000 AD Josephson Junction detectors will be superior to any other device in the microwave and infrared regions
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II SPACECRAFT ANGULAR POSITION DETECTION
We will navigate by the visible radiation from the fixed stars especially our Sun We assume that a useful optical sensor will be feasible using superconductive phenomena Alternatively a Josephson Junction array of narrow beam width tuned to an Earth-based microwave beacon could provide pointing information
III DATA PROCESSING AND OTHER ELECTRONICS
Josephson Junction computers are already being built It takes very little imagination to assume that all electronic and data processing sensor excitation and amplification and housekeeping functions aboard our spacecraft will be done this way
IV DATA TRANSMISSION
Here we have to take a big leap Josephson Junction devices can now radiate about one-billionth of a watt each Since we need at least one watt to transmit data back to Earth we must assume that we can form an array of 10+9 elements which will radiate coherently We will also assume that these will be arranged to give a very narrow beam width Perhaps it could even be the same array used for pointing information operating in a time-shared mode
V SPACECRAFT POINTING
We can carry no consumables to point the spacecraft--or can we If we cant the only source of torque available is the interstellar magnetic field We will point the spacecraft by superconducting coils interacting with the field This means that all other field sources will have to be shielded with superconducting shields
It may be that the disturbance torques in interstellar space are so small that a very modest ration of consumables would provide sufficient torque for a reasonable lifetime say 100 years
Can anyone suggest a way of emitting equal numbers of positive and negative charged jarticles at high speed given that we are to consume little power -and are to operate under 20 Kelvin These could be used for both attitude control and propulsion
VI POWER
We must have a watt to radiate back to Earth All other functions can 9be assumed to consume the same amount Where are we to get our power
First try--we assume that we can store our energy in the magnetic field of a superconducting coil Fields of one mega-Gauss will certainly be feasible by this time Assuming a volume of one cubic meter we can store 4 x 109 joules
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This will be enough for a lifetime of 60 years
If this is unsatisfactory the only alternate I can think of is a Radio Isotope Thermal Generator Unfortunately this violates our ground rule of no operation above 20 Kelvin and gives us thermal power of 20 watts to radiate If this is not to warm the rest of the spaceshycraft unduly it will have to be placed at a distance of (TBD) meters away (No doubt we will allow it to unreel itself on a tape rule extension after achieving our interstellar trajectory) We will also use panels of TBD square meters to radiate the power at a temperature of TBD
LOCATING PLANETS ORBITING ANOTHER STAR
Probably the most important scientific objective for a mission to
another star here would be the discovery of planets orbiting it What
might we expect of a spacecraft under such circumstances
1) As soon as the vehicle is close enough to permit optical detection
techniques to function a search must begin for planets Remember
at this point we dont even know the orientation of the ecliptic planet
for the system in question The vehicle must search the region around
the primary for objects that
a) exhibit large motion terms with respect to the background stars and
b) have spectral properties that are characteristic of reflecting
bodies rather than self luminous ones When one considers that several thousand bright points (mostly background stars) will be
visable in the field of view and that at most only about a dozen of
these can be reasonably expected to be planets the magnitude of
the problem becomes apparent
Some means of keeping track of all these candidate planets or some
technique for comprehensive spectral analysis is in order Probably a
combination of these methods will prove to be the most effective
Consider the following scenario When the vehicle is about 50 AU from
the star a region of space about 10 or 15 AU in radius is observed Here
the radius referred to is centered at the target star This corresponds
to a total field of interest that is about 10 to 15 degrees in solid angle
Each point of light (star maybe planet) must be investigated by spectroshy
graphic analysis and the positions of each candidate object recorded for future
use As the vehicle plunges deeper into the system parallax produced by its
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own motion and motion of the planets in their orbits will change their
apparent position relative to the background stars By an iterative
process this technique should locate several of the planets in the system
Once their positions are known then the onboard computer must compute the
orbital parameters for the objects that have been located This will result
in among other things the identification of the ecliptic plane This plane
can now be searched for additional planets
Now that we know where all of the planets in the system may be found a
gross assumption we can settle down to a search for bodies that might harbor
life
If we know the total thermal output of the star and for Barnard we do we
can compute the range of distances where black body equilibrium temperature
ranges between 00 C and 1000C This is where the search for life begins
If one or more of our planets falls between these boundaries of fire and
ice we might expect the vehicle to compute a trajectory that would permit
either a flyby or even an orbital encounter with the planet Beyond obsershy
vation of the planet from this orbitanything that can be discussed from this
point on moves rapidly out of the range of science and into science fiction and
as such is outside the scope of this report
82
77-70
APPENDIX D
SOLAR SYSTEM BALLISTIC ESCAPE TRAJECTORIES
The listings which follow give distance (RAD) in astronomical
units and velocity (VEL) in kms for ballistic escape trajectories
with perihelia (Q) of 01 03 05 10 20 and 52 AU and hypershy
bolic excess velocities (V) of 0 1 5 10 20 30 40 50
and 60 kms For each V output is given at 02 year intervals for
time (T) less than 10 years after perihelion and one year intervals
for time between 10 and 60 years after perihelion
For higher V and long times the distance (RAD) can be scaled as
proportional to V and the velocity VEL V
83
PRW nATr 03in77 nA1 I
V-TNFINITY 0 KMS
0 1 AU 0 = 3 AU n = 5 AI D = 10 Slt 0 O All A 52 AU T - YRS PAD VEL PAD VEL PAn VFL QAn VFL PAM 1 EL Ar) vrl
00
20 On0 60 80
100 12n 140 160 180 200
1000 18279 P9552 30016 47466 55233 62496 6q365 75914 8P19 AA47
131201A 311952 24s0P9 213290 193330 17Q9p0 1664q3199032 192879 1460P2 141794
30on 16741 27133V 37226 4563 53381 606p767483 714021 80294 86330
76q041 3p95q P2184 21819 1Q7172 182312 I71n71 I6214R 1)4821 14t8651 143399
rnl0n
7Ap F14 39666 4306 9166 8Q
A7P3 7P94fl 7A45 Pq2A
ror-Qfi 3398po P9q1 PP3n 314 POOnI1 1A77 173 06P 164104 1R6718 1S9041 44AR1
innno 1r6 1l 3P87t9 4077A 48107 r9A16 61qn4 6P31 7448P A04o
u91i 1710n P6q07 9323A14 PnAgdegn 10IA66 1702RA iorn7 161161 19411J4 14PR17
P0nn pIfls P6410 3P1 A466
4u7jn -0P39) -70n 6PQ~P 6A7o 7414r
po7aI47 PA41I
95rQn05 45
P1476M 100149 1866 176115 167019 16m067 1544An
qpnn 1Al17 59n2 1Pn3 911=1 tfl906 QitSuI 1oflp jampl40 1 7
CP71n 1nfl 619 Ilq 6 I 9 1 671A iAtA6 7nI gpi7fl 7141 1lt7
220 24o 260 280 300 320 34n 360 380 400 420
94100 q077q
115302 110684 115940 121081 126115 131052 135898 140660 145343
117313 133349 P9805 I6609 IP3706 lP1092 11861t 116355 114262 112311 110487
02186 07860 1337A 101757 114010 11014A 12417q 120114 33998
13S717 143308
1I871 114650 11nO7 197726 IP47q lPol0 I19912 117pP9 115nf7 113oqr111234
n6p Q6n95
10i153 In6900 It21 117R3 Ipp30a 127P30 13P07A 116A34 1411
14012 11r031 132191 1p8P27 I2 77P 1p20A6 IP01449 118116 1150f 113871 11107
A6214 01896 C79POt 106P4 707835 1102n16 117019 IpPA4f j97657tVp3o2137n1
14496 iIOflnO 3n3 1314A7 12A971
saol ippes 190fllP 11743 1157AC5 137Al
7QAls A928 nO n Q9660 jon7po n16a6 jtn9i 1i371
12nfn Ip473A1196 iP311
14Onsq 1447q 140nnI 1361Al IP71q lpoA 12Ar67P 194n1 191
117135
77067 A670 AtW4 POpal ql10 o70 n~nnflf lnfAn-1nn7nn Ijgt19Af7n
jCnpq3 I(9t tamn1n
j~fl0nm7f j8n~f) j3 0Ann
1S1 97750 11
I9r
0 O
O 4
440 460 480 500 920 540 960 580 600 620 640 660 680 700 72o 740 760 780 800 820 840 A60 880 900
149952 154492 158967 163380 167734 172033 176279 180475 184623 188725 192784 1Q6800 200776 204713 2n1612 212476 216305 220101 223664 227596 231298 234971 238615 242232
106776 in7165 105646 In4210 10284B 101555 100329 q9192 q8031 q6060 q5934 q4Q50 Q4009 93007 2223
Q1380 Q0968 9784
896P6 88203 A7583 8l6898 A6230 R5584
148006 152544 157017 161420 16q782 17o8n 17432 17852n 182667 IR676A 1qn829 194841 190816 20P752 206651 210514 21434P 21013A 221900 22563P 229333 233005 236649 240269
1001488 jo7847 106300 In4A38 103492 1n2137 10OS5 Q603 0995 C74A7 06499 094P6 a44F p3946 0269q q1s05 000 2 q0167 89e1Q 88676 A7958 97P62 A6588 A5934
146115 1065 1f 1-51]20 IScq2q 1(3A79 168175 17917 1766in IAn075 1q4094 1 Rl0 100021 1Q6807 2n031 P047PO 2nAon 21P417 216911 219075 223703 2P7403 P3I074 24717 P3833P
110199 1sR3 I068g i516n I04051 1n2714 10144 IoO3 00079 Q7Q07 Q6015 q9qq 64027 q3p q30Q3 q292p
30 WO8A 89p1o 8On9 A8331 87626 86043 6PA3
1411637 146196 190612 19q007190144 163627 167850 h7O41 tt6176 180266 In411 1A17 1nP953 1q6210 200100 20359 20777 211569 21 5In 21004p 229737 2264113 230040 233650
l1l9P3 1l107Q j0nfl37 111609 In9l 1inA1Al 1P27n0 In13 03lq4 00pq Q81114 07nf n6nQ 0n3 041r4 03270 Q4np QI7A 017779 Q0nnn RAQ91I AR599 87893 R7141
131A7R 14966A 147001 1128 tt ij0607 1 38v1 167Q9 171Q7 17rqAl 1700rP If38n3 1A7777 0163 1Q5461 1o093 P01014 20674 210441 214114 2177r7 PP137 P2496e
1179144 1nl 113p76 1patO 11119lpnnp6 InQn6 13ia 1n89QA 1-q6t in6Q1 1in 9 iuaO 14lj i046 1plusmnAQ1A I9790 1snRfs 1f1q2 4398 ifl0q 15ann1 q06 1616r9 08po 16Pf o7lnr t6ao0 06991 171gt477 q5p7r 176041 04164 170-Af Q34146 18112 06A30 186616 Ini lonnn
01030 1Q356$ 00966 107000o R029r 9flnl44 8R888 Pa APl1
11gt01109
jiflq I7 r6n C 1 1vAq leg 1 118 loq0A3 O8l lI9 jn9nAq f41A5 nA
fao6 InI14 iAlnp2 onfol 08ij
0Cfl7 06fnq
074f
0U40 obtnA9 01A
920 940 960 980
1000
245822 249386 252925 256440 259931
84957 84347 83755 83179 82619
24385c2474lq 250957 254471 257962
A599 84692 84083 83500 82934
241021 249484 2490n2 252934 256024
Aq63080n1 84400 83A20 83247
217P34 40791 24U326 247A35 251320
81618 8583q P16
R4611 840P2
22ASA 23P064 23t570 P39fl7fl 24253A
88113 A7430 A6784 8614 830
po p71090A pj1qf 2IMP4 P20680
s0e oIn7 OInA5 Qf 4 A462
2 PRW nAT 0I3077 PArF
V-INFINITY 0 KMs
0 = 1 AU G = 3 AU q = 9 AU (4 1= AU 0 = P0 All n = 92 AU T - YRS RAD VEL RAD VEL PArl VEL PAn VEL PAD VEL PAn Vr I
1000 1100
25Q931 277048
82619 AoOn26
25796P 275077
82q34 80312
256024 P73139
83P47 A0qq7
PS1120 p6A41P
84022 82303
24P51P pqq5j
R5930 AP67Q
Ppn6n p36031
m6fp At36
1200 293653 77730 2916R1 179q3 PPQ36 78p54 IA4QQ7 7Rqnp 27A06 A0169 Psi IPAAA PWi
1300 1400 1500 1600 1700
30Q803 329544 340914 355946 370667
75677 7382572142 70602 69186
307820 3P3568 338937 353g68368680
79o20 74no0 72352 707qQA937j
305ARt 101619 316989 392 4 366733
76161 74P74 7261 70oq969556
1011pq 116893 33P2n9 3T7P22 36103Q
767I 74A31l 73Al 714A3 70019
pqP14 3fl7M 9 3P31PO 33pl93P77q
7701 79021t 74101 7P441 7ft018
P64A PR611 2qp6n0 31p327603
0ItQQ ftqA77fA4 75001 303
1800 385103 67877 383124 6805P 381166 68p2A 376364 6A660 367171 6Ql4 3417n 97 1900 39q274 66661 3q7294 669P7 3q99134 66n09 09P9 674n4 3AIln4 6214 1996nn 0636 2000 413199 65528 41117 65686 4nQP96 6SP3 404441 66P14 Q0910o 67009 3606 A01 7
t 2100 426892 6446Q 424911 64619 49q4A 64769 418I17 St4jr0419 65o76 31712P l 2200 2300
440370 453645
63475 62519
438388 45166
61618 62676
416425 411960Q
63761 62813
431 R 444R66
64116 631C3
4P01 41q94n
64818 A3n2r
3Onin 4nQ0l7
seoq 6CnAI
2400 2500
466730 479633
61696 60821
464747 477690
61797 60947
4APA1 479684s
62I1 An73
497n44 47n842
6PP49 6 I6
44A6n7 6124r6
AIQAO 6Pn09
-4p101i 41t690
91147 6900
2600 492366 60029 4q38 60191 4AAR19 60P72 483970 60r73 474q17 61169 44729 6on6 2700 504937 99277 50993 0304 900OA4 r~Ql 4q6139 RO l 4867a6 Ai7r 450641 6O19 2800 2c)O0
517353 529622
58962 57880
51r36S 527637
98674 979A8
91314a qP9A6A
98787 98007
5OP947 92fl 11
99q67 83A7
4q0141 t133q
rqAp1 9ofl
47 3I 4A4046
oi 17 Anr43
0 3000 3100
541751 593746
97p2a96605
53Q766 551761
r7V3 96706
5377q6910790
9749 560nA0
S3Q36 r44Q7
7e6qr706t
SAs0 9394RI
sRagt17 S796P
4q6007 r n
qpr6 913
3200 565613 56008 561627 96206 561656 969n 596740 6490 547134 56nl3 910671 sRfq1 -
3300 3400
577357 588983
55435 548A8
579371 586996
55531 94q7
571 QQ 9n503
r5626 5n71
96A30 98019p
590A64 9532
q5qn6e 9r70674
r635 99790
r913nA 94R
p77 8 0 i1
3500 600495 54397 598508 94447 5q6935 94c37 901661 94761 9AP173 9on0 r54246 6c79 3600 3700
611898 623196
53848 53398
60q9ll 6P1209
93Q36 93443
607q37 61q959
94023 392A
603061 614356
5424 r1740
5q3561 60484Q
94671 r4161
99s96 57676R
6n1 t44
3800 3400
634393 645491
528A5 r2428
630409 641504
9296A r2509
63 0431 641929
93052 92990
699590 636646
93p7 997Pj
616014 Ap 7 1pi
9ils66 5110o
9A7817 qA8Q9
q4fl97 944l0
4000 4100 4200
656496 667409 67A233
51987 51560 51147
694508 669421 676245
52066 91617 9122
652q3 66344q 674269
92144 91714 9IpW7
647648 698958 660381
9P141 91oo 914R4
618115 64OIA 6q39
52730 5ppA9 519i9
6009p 6pn661 631419
C fn3q ga6 9Im0q
4300 688973 50747 686984 rO8O 6A9o0 50893 680118 92n76 670562 9143 642086 r67 4400 4500
6q9629 710204
50359 49982
697640 70A216
90430 90052
605661 706238
50902 90122
6Q0771 701345
906A1 nn7
6Pl0O 6q1776
9In35 5n644
69gt617 66X1P
iq C1794
4600 4700 4800
720702 731124 741472
49617 49262 48917
718713 72Q135 739483
49686 4932q 48983
7t6736 7P7157 737905
4q54 49396 49049
71I41 72P61 712607
4QQ5 4Q963 4021P
70P2e9 71P67q 723fll
9064 4qQ98 4qWi7
671697 6A000 694p
9 A C103 1 g09 9
4900 5000
751749 761956
48582 48255
749760 75P966
48646 4A318
7477R1 7q7087
48710 408381
748RP 7930N7
48871 48R548
733288 7434A8
40lg 48R91
7n494 71e60
n 04 4qnA6
5100 772095 47937 770105 4790q 768126 48N61 7632P4 48219 793620 4A891 7P4747 4047A 5200 782168 47628 78017A 4768 7781Qq 4774q 773209 467Q00 763686 4800 7A477P b014n 5300 792177 473P6 790187 4735 788P07 47449 78303 471O3 773688 47A88 744711 6A810 5400 5500
802123 812007
47031 46744
800133 810017
4700 46802
798153 808037
47148 46P85
7q3P47 803130
47PO4 47n02
78162A 793906
4793 4706
7r463 76443
a014q O0176
560n 5700 5800 5900
821832 831599 841309 850963
46464 46190 45923 45662
8184P 820609 83q318 849972
46520 46246 pound5077 45715
817A62 SP7628 S37137 846092
46977 4601 46032 45760
qt1qS4 827tq 932427 A40080
46717 4643q 46167 49Q02
80133 813n6 P2P7q0 38143
46q6 4613 46437 461A7
774P9 7R39fnl 7q1640 80j32I4
U707(0 Tg72 7R2
O6098 6000 860562 45406 858572 45499 856590 4591P 851678 4643 842033 450l3 812826 4671
3 PRW n rlp njiN77 rArr
V-INFINITY 10 KMS
q = -1 AU 0 = 3 AU 0 = 5 Alt n = tn Alf n = 20 All A = SP Atl T - YRS PAD VEL PAD VEL P~n VFL_ PAn VFL PAn Vrl mAr) Vrl
00 1000 1112090 30nn 769tn3 nnn 90577A J~nnoln up11AR P~nnnn POAnic tprnn lnnq7 20 18283 111677 1 674 9661 1 7 1902A 196in 137p n 211 61 PAcn6P SpaPI U47t 4 0 2056) 2451119 2784R 2-263 P6439 P9QO6P 241IP P60712 264rp Pr01Al Tlnrt lnPnAp
1-00 9926q 179450 93417 1A25P9 17pp lAar4PI 4APIA lompnliq 4u7AA 1qgto rmA711
140 6q42t 1A0181 67530 IAP3AO rV)TAn IA4q3 6IA1001 11 - 711711 17A~ng 30 16n 759amp1 153138 74nRp 1-i5041 7PXnP 16064 6314 16IIQA 6nnc 16A1nA 6ibq I 7 160 20n
AP273 SA357
14719IP IIt2074t
A037P A64Pq
1411919 1436P6
7A974 A0IlF17
19OAII 11 91 4A
74q6p P03n
Io ip 1A767
6A7ar 7 111411n
16Mqn3 I 47n r
7noP7 744i
1=Af7 I M400
P2n 04202 117601 gppn 110ql 01146S |4niinp RAAPO 14171A 7nnrn f400AA 7AOn6 191mro 240 qsq95 113647 Q7979 174naP n Al11 I16nIA n1044 1X~qp7 r360 1UqIIa1 A Ipit laKm 260 105429 110111 101506 ji1jn7 int661 112489 Q74 j1 t1 nnian 140 1- ArAla l(I nl 280 110929 116Q3 1OS89A JP904 ln IfI7 lpq15n ln7(n 11177r 0 -p 6fiII tnr I I tlt 300 116095 JP4029 114169 1 -5065 llPin7 iP6nRp tn7003 IP1156 lnnAq7 1IPOA4 q1 110117
340 126297 lIS946 1243AP 119A62 IPP~qP 1111767 I1ftI jppnA6 1111771 IP6094 ln11lo a 360) 131249 1166Q7 120310 1179(2 1P7436i 11-RUIA ip3nao IPn4 o n 1 1P4nn o IT nI43 38n 136109 114610 13416n 11543n IIP qn 716P41 17n7 IIAP17 12nS16 IPIA47 ipqQAR 09nmlz 400 I4nA86 112666 138944 11344 117ns0t1 141 t1067P 1IAnC6 lPUQ77 t1o001171 11q99 420 149584 110S47 143641) 111spa 141 R 11ptP3 1Pai 11411A 1Pq960 117U46 11A7An 440 150209 10-914 14A263 inqs5n 146173 110991 l4jAQR 11PP6 jjan~oA 11qU61 ipnfqu 1q6r7
480 500
159255 IL65684
In6023 1045Q2
157306 161734
1n6672 109pIr
lqtLnq 19QA34
in711f InrA 3
l nqn4 15r-1t
inAnop 1n7149R
14P960 171pi
11l[PWI 11010A
1PP17A 1 Oq ii74g
l
52o 1611059 103216 1661nl ln3nq 164pni I I 14142 150660 1 nP 1-1610 inAA17 ilroii 114rl 54o 17P370 1n1947 17n4 17 In294 16Ar13 In3n97 163Qq9 1n4rnP 199866 In7iqO 11014PA l4nQA 560 176633 1007P2 17467n jnl7A 17 777P 1nIA3n 16AP17 jn1llPIA 16n(67 fnV797 14i6na 111r13 58n 110846 q9993 1788qtI nOO0O 176npp In062i 17P416 InI143 164Ppn 11144P 1471(n jinipt 600 185011 98438 1A3099 qSq97 1S1144 o9 7P 17696AR ln074A 16R3Pn 10 11q trinaa 1AA14 620 IA9131 07371 18l7174 07Ft73 18P61 QA 7P IAn679 Qqno 17P3QsA 1n1n40 itUO ln C1 640 193206 Q614q I 121to 06p6 1Aq133 Q7A1a 184710a o no 17045) Inn~p 19 A4A 1nA174 660 197240 Q5370 1992sp q5A4P 393165 Q6tn 1AA76P Q74A- JAn nA CQAT5 1A9 oAa lnrn~r 680 700
201234 20518l9
94429 9395
lcl027q 20122C)
qRA 7 n597n
19719f PnI Rn
q9 4P 0441
19P74q Iof660n
Q64Ai Q-n
IR 197 1sA26Q
ag ti Q79Q1
16q817 16o444
1mqn14 In9016
720 740
209107 21P989
026r5 911116
20714A 2110vt
OAnR7 Q2217
pn9pps 21101I05
q5qt7 Op655
pOntqo 204472
o477 00 647
10Pl47 lqqn O
06A10 00f7
17 )n 170261
a1 jnnll
76t0 216q37 01008 21487q Q141A pIpn50 qlpI 221111 oPpl0 Iq)O61 047r 1AfOlQ- OMA() 780 S00
220651 224434
902P7 A9473
211688 22P470
006gt7 A9862
P36763 Pp 541
q10Pk qOIP4Q
P10117 piqsot
QPnn3 Qtpnc
pnlrpn pn3po
Q1RQn oIn7
1P1741 11170A7
OR775 0pri
820 228185 A8744 226221 A91P4 PP4p9l R9MI1 P1Q639 Q04I3 Pllfn4A lop171 OAn 6i 8l40 231906 98038 27Q941 AFtOq pp801P AA777 223140 R406 A pi473A q1446 QoaAno2 060 235598 R7395 233633 A777 23170p Fl8077 27134 AAQ66 piA~on On$96 1qdeg7n 09 M 880 239262 86692 237296 137046 P19164 A7t9A 2-Ioflql RAP67 2PPOq FIqo4Q Pn1AIof 444 900 24289P 96050 24093P A6399 2311099 86739 2343PI A7rot 2256all AqP3F pOuo9 OtO 920 q40
246508 250092
n5426 94820
244941 248125
Ft5764 P5191
24 P609 2961q1
A6100 85480
237q24 241tin3
86942 A6P94
2202PR 2IPA6
AFtr49 A774
P0p0nn 21i3on
GAOA 0911Mq
960 253651 84231 291684 A4s55 P4974A A4077 249056 A9675 236321 873 21476I 01491 980 257186 83658 25521A S3976 29IPS2 A492 248555 A5073 25qA3p 56rq0 PI117 OCM4 1000 260697 83101 258728 A3412 P136791 FI3722 2S2091 Rdeg44AA 2433pnl 95096 2149- Onoo6
IATF 031077 PArr 4 PRW
V-INFINTTY = 10 KMS
0 = 20 All n = K2 AU VEL it VFL AO VFt pnf Vrt
a 1 AU a = 3 AU 0 = 5 AU a = 10 AU
T - YRS RAO VEL RAt VEL RA
R372P 2Pfl9 A44AF 2l4 n A1176 2p1455 ofnlf6l 1000 260697 83101 2587p2 83412 P9671Q
pAf 4 38 R3Yl14 P11na 0tAP74007 A108R P6qP Al7A5
A0n646 ps-RaIA AtlS1tIN1100 277918 805P4 275947 80806 2 7
00 1200 294630 78243 2q2659 7 f0p Pnn714 7 R76D pRr978 79309) P7710g9 76681 30PPPO 77p71 Pq3546 7A4R gt60610 A135
1300 310890 76204 308917 76443 306570 791r5 3fl058 764pq PAuqn Po97
1400 326744 74365 32476Q 74s86 32plq 74807 IlAfl 75618 37P44n 7421 30onl 0
1500 342229 72694 340251 72(91 338301 73107 33199q
1600 39737q 71166 355402 71360 351448 71i55 34A666 7P03l 33Q956 72074 34767 T1741 3543r1 71464 32n56 4nno6368PAR 7012r 36247 7fl9771700 372222 69761 370244 69)44
3447 76237046 6A233 36A66 70n71800 386780 68463 38480P A636 38844 68807 678a4 1q2112 67q9n 3A31 ApFs Ir7r5f4 v111R4
1900 401076 67299 399097 6742 3P73 3Q7130 67qP4 171lo9 AOa47
_X 2000 415128 66136 413148 66ql 411187 66449 4n6375 66p2 65746 410ll0 66465 3RLA4 AQAo
2100 428951 65087 426970 A5p34 0500 6snl 42011 438617 64t83 4317q3 64711 4P4fnQ 6r41A 3Q826 67401
2200 44P561 64102 44058 64242 47901 6439 411466 AU 3
2300 455970 63176 493qBA 63310 450pl4 63444 4 1Q 6377
2400 469150 62302 467208 6P431 465rP4 62r9q 460409 6PA78 4rtOAt 65A08 4Un4 A54q A43
2500 482231 61476 4S0248 615Q0 475A3 Ao172P 471444 AnPq 4641n A234 437360 618n6 11067 61r760530 liA6311 6l9J4 4769s12600 499103 60693 493120 60811 491153
Aq649 61n2 467695 A31 q5719 q0pin1 60P75 47qO4n 9 o972700 507815 5049 505831 60063 -nf3864 60177 4qcnl8 60461
2800 5P0374 59242 51A3g0 9935p 91642P 9qP6 9117p RAYO780 Or43
545063 97QP4 543078 550P6 94110q 9812) 536P9p 58303 PS6814 58088 4904A95 $nu342900 53788 58567 530804 58674 528835 381 14976 5qr6r5 48711A AI1A
3000 57r06 945l51 57759 qlRqAn 5R41 9114Al7 nllr557206 57308 559221 57407 953o19
9P13SQ r0f6 13100 3200 569222 96718 567237 56815 96qP66 560j0 560403 s7t4q 99nq60 s7sp
57PQ4 56971 56PA4n 57npq 53v17o 914403300 581117 96193 57q131 96246 577150 9613) 5840A6 56016 s746414 56461 9q6A8t q7p32
3400 592895 55611 59090q 95701 588937 55791 5548p 586797 c014 55A4Pn C71A$
3500 604561 55089 602575 95177 600602 55264 59973p 56QPA6 g6Anr
3600 616120 54587 614133 54672 612160 54757 60787 946q 5q78l i59RQ
627575 94103 629588 r4086 693614 94P69 61A739 54475 6fl024 54084 S8I 3 gA1473700 3800 638930 53617 636943 53718 634q6q 9 i9 6a0q 53Q 620588 54357 5(9553 FA7
641347 99S 631V 3n7 Ani7nl K173900 650188 93187 64A201 53p69 646P6 59544
64Pqn 9347 61478Q 9( 44000 661353 52752 650366 5pp 69731 5p200 6qPI0(I 30Q5 4100 672429 52331 670441 9206 66A466 rP4A1 661RAI 52666 Aq4nq s3o3 pF701 9u178
66fl3l Al611 6$A7fln 97 4200 683417 91925 69142Q 5IqQ7 67()454 c2fl7n 6760 5P1
rRK70 1Pn 67r5A 90n1 6479415 Rnj4300 694321 91530 69P333 91602 6q0357 i1673
4400 709144 1148 701159 91218 7n1170 S1287 6Q629l 91460 686741 91983 AqR30 5Sn0
4500 715887 50778 713858 90846 71192P 50014 70fl3p 5 1083 65747A 5Jt18 66PQAP 96l rOnA54600 726553 V0418 724565 S0485 72PqSR 50591 717606 50716 70814 nt04 67oSAR
4700 737145 50069 739196 )nl34 71117C) 09Q 728986 5061 718717 511482 65012 - 1Al 7qpP 50330 f7ln9Ag8 910qR
4800 747664 49730 745675 49794 7436q8 4q057 738R03 50015 4900 758113 49400 756124 49462 794146 4-q24 74qP90 4Q670 730676 4qA97 71oqfl Cnn46
768493 49079 766504 49140 7649P6 4p0ol 7996pq 4939 79NNI03 q6g4 7P135 n05000 5100 778807 48767 776818 4886 774539 48P86 76q941 40039 7601n 40140 7A1971 Kn95
787066 48521 785089 497Q 78f0IPA 487P5 770501 qnoi 741771 nIQ5200 789056 48462
79725P 458P3 705273 48280 7q037P 48(424 78077 (k708 7 9jQ0(q 4mq5q5300 79c241 48166 5400 A09365 47876 807376 47033 805396 4-7ofq A004n4 4Rtn 7QnRA0 48408 7A1QPR 1107Q
8I9u6 4770r 811156 478 Ron9r 481t7 77007 4An7p5500 819425 47994 817439 47650 4793 7810Qq 4OA75600 829434 47319 B27444 47374 809464 47428 RP0960 47q63 81044
80R6 47r55 7q1879 Un 9 5700 8393R2 47091 8 73qP 47104 83541P 47157 R3006 47PQo
46P9 840307 470P4 83n77A 4783 Rfn17P7 4P8045800 84q274 46788 847284 4681 845104 5900 85Q111 465s2 857121 46r83 P59141 46635 85033 46763 84n604 47n18 8115 17016
467q tp1271 o7436000 868895 46281 866909 46312 864024 46383 860015 465nq 850383
PRW lAir 6114177 nAf~r O
V-TNFINITY 50 KMS
0 1 AU 0 = 3 AU q = 9 Al 0 = Al l A = P n All t All T - YRS PAD VEL PAD VFI flAn VFL PAD IFL P~nff VpI PrA
00 20 40
1000 1A394 CI814
132q90 101660 P49010
3000 165 28103
770661 328300 2561l
5n00 lA91 P607
q7789 33-8296 P62P
IOnnn l9A7 17 247 0
4P4176 NI047P PPas7
2n0n P1I0q7 26750
3nPnl9 PpAPp7 P6p05
gi nn svi014 r1fl1
101F4 iQnn6 1lo14
60
80 10r
3q465 48124 96110
P17847 108414 194706
376Ak 463nr 5427
PP2671 2n2nl2 I8t75q1
3618l 4467A 59q=
P2714P pp 547 10p53
31109 41919 40166
P35PSQ P1PAOP InA4 7
380 npao
43A p1A901 nno06
r 1 M sO6tP
0Th76m4q4jO i7 OnO
120 140
63624 70750
174317 166066
61761 68875
176711 1681n
Ann47 67112
17flnjQ 17onsA
5A431 6017R
j8IRttOMa3O 17469P 5P645
0 4 Ip0anp
6P614 lAgnftl 1A711
160 180
77567 84127
1592Q2 15351
7568p A234
161070 1q5163
73l7 A04P
16P7 P 1q6606
70n-6 76905
16681P Irn0p6
64AFv 7002
17274 16587A
6n4A 721 -
jA7TFL igiS06
200 90468 148701 88569 1r 01 n 86771 11ampA3 q55 1S47P9 76860 j5Qo44 711 e7nq
220 240
96621 102607
144440 140683
p4716 1006q7
145714 14144
fP 0Pf70
165 142081
PA$n ot751
1j 0alP 14A6A
Q26a4 lPRS
54784 1jSfo
A11111 8g)
qAnac 191A77
260 108447 137334 10653P 384Ano 104705 110446 100r4 1410a5 01077 146V1A P04k 1101C6 280 114154 14323 112236 135308 110n01 136)76 In61-1 385 o4ra 14PnQ qA74 1jAt07
500 119742 131r09 117520 11251n 11507 11341n it171s 115s a n4867 3I 0704I 03Nql 320 340
125221 130602
129108 126R28
123297 128675
1p2q96p 1976P7
jP244q 1P6891
13nfnP 1P2414
117176 1PP2P1
l3Pp8P 1n12
1107n0 l15940n
136109 133o
7099 ItSIVl
n0nnQ 0q
360 380
135891 141096
I47P6 IP2780
133961 139164
1P5477 2P3480
13P101 137301
1P6217 1P417
Ip7770 113gt99
1Ann5 jPsA76
Ipnrr n
1P56uo 1391913 1P OP9
Ill~na ll1iq
16nR I kqiA
400 420
146222 151276
120)71 1102A4
1442A8 14034n
1P1641 11q19
14P4PP l747n
iP2nP 12P046
13A055 143085
I23oA2 1PP66
130656 1Ij606
1PAnn9 IP4Ao
1104A7 Ip7A6
Ij191 iOM9
440 460
156261 161183
117705 116223
1543P4 1244
1183nO 116740
15210n 157167
11Ao05 117365
14804 500
1203lX1 14 l4Q7 IPPOOA8 8511O4Y14911 i21p9 7
lpPOo t 1p A
jV7ofl7 A 3
480 166044 114828 164104 119177 16224 11501A 157702 117P16 15h1q 1166U 13F6n9 I 500 170849 113512 161908 114036 1675 114q54 162570 iiol 194941 115146 14nP 9 1 oA A 520 175601 11267 17365A 112770 17177P 113P66 167114 114474 jrap4 1161j5 14tq00 1IA4
540 180302 11101A 178357 111970 176460 112045 171cq 113p25 1641tp 115961 14030n 110043 56n 580
184954 189562
009q68 108903
183000 187619
31043t in9148
181114 1S57P3
110PA 10Q797
1166i 1A121
11pnn 11n60
16871tn 171Pa
1 Unn 26
I on 26771
600 620
104125 108647
107318 106910
1q2178 19669q
1n8316 107332
1on8 q48n0
20S740 10774A0
A978P 1qp2
10n773 10738
1A8n 1RPP7
j117n7 11060n
613A8 16A O n
I no1 1nI46
640 660
203130 207574
10593 105107
201181 205624
I063qP 1n54q2
1q9p2p Pn03P4
106786 109P73
104761 IOnIQ7
In7740 6n
10671 191111
10cR6 101qq4
17n010 174208
11171 111060
680 211983 104298 21003P I04611 20130 I04OqQ on0504 ln0Ao0 10947r In7Q945 17PP04 11589 700 216356 i03444 214404 1n3804 p1p5n1 11416n pn7T0A 1n5n32 1aaAnn 106A76 180361 1n086 720 220696 102661 218744 103010 216830 111136 PIPP8q 04Pnl po41oq In9706 18441n In607 740 225004 101000 223051 102247 PP1145 0PqA8 p699R 0101 pfl0A370 j04qs Ign44 itAn4 760 229281 101189 227327 101513 pp5420 101838 pp0PR6 IP613 plP6pn 1041q 10449i 107R16 780 800
233528 237747
100487 Q9814
231574 23579P
10j009 1001P
PPA65 P3388P
1011P 1004f30
ap59 PPQn6
01803 In11Ai
- 21683 2p1ol0
1n37 10PAn4
10944A 904949
InA l IAl7
820 840 860
24193A 24610 250240
09164 q8537 q7930
23998P 24414c 248283
q)465 q8029 qS15
211071 P42P33 2u6370
Q9763 40110 Q8t07
P3349q 237646 P4177
Inn0f0 QQ30 Q0189
PP917n pp43lp 2 334PP
101p87 10118 inO01
20A3nQ9 3nAI
giu2pq
iot14 1nuT4 1nIP
880 254353 07343 252396 q760 2504I1 97899 2RA4 0Rc q 2375n7 0QAS jPIA4 I InSI 900 920
258442 262507
96774 96223
256484 26054)
Q7044 96487
PR4569 2R8631
0731p 9674S
40Q67 254026
o070AQ Q738q
P4156n 2456n0
oappO Q61n
Pp2058 2p=Q0 6
|nP4 l 749
940 266550 95689 264591 05Q46 262674 06P01 P58063 q6RP6 24A6 0q018 2p070a I1noq 960 980 1000
270571 274570 278549
95171 Q4668 94179
268612 272610 276588
Q54PP 04913 04418
P66691 270691 P74660
q5670Q5155 Q4655
262n78 P66071 270045
96PR1 5791
02P38
2R3614 257601 P61557
C7445 06o0 96351t
231644 23747e 14P1P
A
1104R8 GA 6 00063
6 fArE 0V077 PAFPRW
V-INFINITY 50 KMS
0 Z 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU = 20 AU a = 52 AU T - YRS RAI VEL RAD VEL PAn V aAn VFL RAn VEL Phn VPI
1000 1100 1200 1300
278549 298149 317306 336074
Q4179 91929 89993 A8201
27658A 296187 315343 334104
q441A Q243 90147 n8377
274669 Pq4P63 913416 332l7q
q-46r Qp1 90338 A8551
p7O49 2nq6l 3nRAA9 127s08
Q9P3 Q677 90810 ARqO
p61S7 P81097 30f170 31AAP
Q6121 03n77 q171rAQon5
P41PQf P6nlFP 27oAAnq 29A931
Q63 o~q9 04161 OonA2
1400 1900 1600 1700 1800
354493 372600 390423 407989 425318
86632 A5216 83931 82797 81680
350527 370633 388459 406020 42334A
P67q9 A5965 84068 92A99 81799
3509Q9 368698 3A65l4 u04AR1 4P1408
86Q92 89512 84pO4 A3011 A1016
14q0ij 364n04 981815 399370 416689
R73-49 89874 8k491 n33P3 8207
33717A 35527r 373000 9n51q 407807
RAtfl9 8657P RqI6 83925 A27A9
314RPI 33P978 fn0o 36P71 9pen307
0nqp PAr 5 A3nq Pg 1 Ai1t$
190n 442430 80686 44f450 90797 43991A8 AOOR 4337Q1 8116O 4P4AA 817n6 4n15 890n4
2000 2100 2200 2300 2400
459341 476066 492616 50Q00 525242
79766 78911 78113 77368 76668
457370 474q094 490644 50703P 52326Q
79870 790fq 78206 77495 76791
4994p7 4P14q 488690 rn9086 9P1321
70974 7 noe 78248 77r4p 76833
45n64 467411 49I9K0 0 fl37
q16561
802pq 703147 70P9 77797 77n17
44175 498491 47497l 4qI335 S07947
8nP4 7q413 78065 7A173 7710
41v81t 434110 45n69 466865 4p8 f
IA7 01 rs ftnol 7oT75 Dqs
2500 2600
541337 557297
76010 75390
539363 555322
-16089 5465
917414 51373
76167 795c40
932697 4 6t
76361j 757P4
99361Q 530991
636 7608
4ofl857 914665
77804 nq
270n 573130 711Aos 571195 74076 96909 74047 56444n 7 r 1gt Sq5370 79463 93A3w7 TAui5
0
2800 2900 3000 3100 3200
588844 604444 619936 635326 650618
74250 73725 732P6 72751 72298
586868 60046A 61796Q 633350 64864P
74319 737q0 73p88 7211 72196
9A4ql 6n017 616n0 631397 64668
743A6 7385 73ilg 7P87 724t3
9A0149 iqi744 61P133 62661q6410n7
74954 74019 7353 73017 75r4
571064 986647 6nt1 p 6174q661077N
74879 74376 7Afnl 73903 7PAPA
54 tq97 96141 R7677 599066 6oP4
7Cn58 1 71A73 74t4 I9S93
3300 665816 71866 663841 7192P 661887 71076 657103 7P1t2 64799 70176 622 7 0O 3400 680928 71454 678951 71507 676007 71560 672210 71600 6630ss 7I44 6337n FrAq 3500 3600 37OC
699954 710898 729765
71059q 70681 70319
691977 708g21 723787
71110 7070 7066
6Qr)02 7f606-721 A1
71161 7f)770 70411
687233 70174 717n03
71296 7nqn9 70530
67R06A 6Qinni 70795v
7Ist 71139 707 7
69p30n 66716A 6g199
7V04q 71a9 q
7296 3800 740556 69970 738578 70016 7366p 7On62 731R7 70174 72P616 7fl994 AQ6666 1n41 3900 759276 69636 753298 696R0 791341 69724 746544 6QR8 737349 70049 711311 fA71
c c V
4000 4100 4200
769927 784512 7Q9032
69314 69004 68706
767944 7A2533 7Q7053
6q397 69046 69746
76509P 7Pn76 79S9nqs
690Aq 6Qn87 6876
76110 779774 7qflP
6Qr5 6q189 688811
751986 766560 7A1072
6qfl 6937 66477
7pr5o3 7Tn410 754A66
70t5 AQ04 6nr 9
0 4300 813491 68418 81151P 68497 0Q9r4 68496 Ag474q 68501 7Qr51 68777 76oPe3 6008
bull
4400 4500
4600
827890 842232 856518
68I40 67872 67613
829911 84025P 894538
6817A 67909 67648
823Q09 838P94 R257q
68215 67049 67683
81q146833486 847770
6R3fl8 6A0vS 67771
gn09tp 824245 83A5p4
6A480 61gtn 67Q04
7A3603 7976m7 81P211
g93 AA9 6tjU
0 4700 4800 490O
870750 884931 899061
6736a 67119 66884
86R77 882951 897081
C67306 67153 66016
86611 RRfQqP s99121
67431 67186 66q49
6ao0 R76179 R9008
(7515 67p68 6702o
9A971 a6q5p 881045
67681 674P9 6718A
RPApaq R4nP 854q0
6oil7 Af 6764q
5000 913143 66696 911163 6668 9099o0 66710 o04988 66707 898110 6694 86A54A 6vtlf 5100 927177 66435 925107 66466 99D36 66496 qlR4PO 66572 90qt47 6620 880932 67160 5200 5300 5400
941166 995110 969010
66221 66012 65810
939189 95312q 967030
66251 66042 65899
9372 Q91168 069069
66780 66n72 69S67
q3P407 Q46190 q6024q
6614 66143 65-07
9231p4 Q37n6 Q506
66tq4R 66983 66074
946 fllAI7 9P417
es6 6670 6A491
5900 5600
982860 996687
65614 65423
980880 9Q4707
65642 65490
978q27 qQ749
65669 65477
974107 qR7923
67I8 A943
0648t5 q7A6p7
65871 65671
q3n055 Q1R35
AA$f FlVdegn6l
5700 1010466 65P37 1001485 65264 1006523 629n 100700 ers9s qop4ng 694R 6557A 95860 5800 102420 65056 1022224 6508 I02096P 65i08 n543 65171 1006134 6909 07027Q 65064 5900 1037908 64880 10359P7 6405 1033064 64031 1oP9140 64002 iOiq6li 65i13 nqPQ46 Au4 6000 1051573 64709 1040592 64733 1047630 64798 10428n4 64818 1014Q 64037 10n6977 A6oAq
7 PRW nATP 033077 PArr
V-INFINITY = 100 KMS
0 1Al) 3 A(I4 5 AU n0 10 Al) n =20Al A = 90p Au T - YRS PAD VEL PAD VFL PAn VF[ PAt VFL VrFL^nD~n VAY
00 1n0 1335761 300n 77512 tnnn 6n04npq 1lonnr 1PP7 2o0n 114R16 9nfln Pt0fn4
20 1n606 iP3AAP 171A 11617 16P14 4qrA7 - 161PA P08 94A1 pnnE44146AIP 2Q0941
40 30591 p60767 28909 P67196 P7q4 P7p780 pq66Q pP12p5 p76q 22j7 581 7070
60 4078q 31207 3903P 154qp N7528A P230po 3T09o~ P46q09 3s4pplusmn 947A04 CnoP ptin80 50056 213170 4826 P16248 4A67A P1011 4IA71 99807 417nn 5P69093 pnn4100 9870PI 200594 568A~n 020amp8 CrP85 205208A r1 Q3 P1flfln 400It p11sO74 693116A IOA1412n 66912 191oq2 65076 l3lfl 1A qAnt 9qO67 IQ1AQ 5A233 pfln13 6A9l 1011A6140 74771 1A3695 7pq p 185P26 71pp6 186A41 6766 1Qnp8 61371 1o4011 7n3 07An160 8P354 1776n7 80498 17gfl2 7P77P 80330 7in6 1A1567 7AfoN 187690 7F1A 10131P180 A9709 172q63 87814P 173777 86708n f$74041 AP94 17607 7PQ7 18193 7odeg$ 11Ot1200 96871 168273 q4997 t1deg343 03pqfl 17q73 A04PO 17P747 84000 176350 8U1IA 17217220 103868 164966 10j1aQ IA5 1 q nP38 166430 Oo6315 168Aq6 on77P 17jpr onfl 9 Om 240 1107PI 161321 10n837 36217c 107n68 IA3n07 I03141 IA401 07jAn IA7on4 QRPAA 6016260 117447 IS89452 IIq55 1qQP8 11178P 19qofn InA16 i6I77n 103IA 164RA5 lonI0tn A65f280 124060 155800 120160 16Qn 120nn4 27PR4 116A8P 8A0n7 10)2n 16I10 lo= A19 9300 130573 153585 128678 1542 9 1687 ss6A t2pn8 I86vo 1166p 587Aq 1119 9 AInl320 136994 1914Q7 13006 152nQ6 111gog IRP677 12OP37 iufl 12P2o0 1rAX6 f166qo euron77340 143332 1405o5 14143P 150150 I0630 906A8 j3q94p 181084 jp0orn 191tno9 jp9no7 Ig66A31360 14Q595 147853 1476P 14836q 14qPp t4SP60 14177- 1qluQ I152P8 9Pnr54 Ips7ni 18a46380 155787 146290 1-38A 146731 t9Pn71 14710 t470n 14n8n01 ju13on 1987 A30017 tno400 161916 144768 16000q 149pl RAlql 4569A 194n44 U66Q0 473 14A167 13ofl7 1 go7 142n 167984 1433 5 166076 143817 16497 34428 160lo 0 145 0q 5Inn 46p7A 14Rnl 1ftn~440 173998 142116 17P0R8 10914 17n68 lflfl0o 166n83 143816 1nplq 1454 140PI1 l-n i460 179960 1409O3 17F048 14PQR 17 1466 42927 165110 44033 154653 Aj348D 18873 139805 183960 140160 1802132 14n8fl 177QPI 14193 170088 142793 160nMA 70 In9 4500 191742 138756 180827 I109p 1870o6 13qu1 t3771 401a( 1767A iais 16c4A4 03n4 0520 197568 1t7770 lQ9652 118018 IQ1pla 1RS9a AqqP3 l10146 1A25p20 l4441t 17nA8O Iir4540 203354 136839 201437 11714P 1oq6n1 137437 70838 11141 8RP4A 13Q074 17621n 1t 6R
209102 15960 207184 136240 Pn9146560 16q3n pO1080 11710n 10101o 110117A In16a 1nn5580 214A14 135128 21P895 1154n3 211059 13q671 067AQ 1 nn56900 11741A 1nln6IQ05on 1R6QAg600 2pn492 114338 21857P 13461 P16730 214n7 P12459 11q467 n52pA 13654A qOfn7 10688620 226138 1335A9 22421P 113R4Q PPP174 1340AR 2180o0 3466A p08pn 13qn4 197637 17c8 640 231754 132875 22083p 113116 2P7087 1j35 P21609 o33a0o p163o0 134o 4 P0pq05 16o0660 237340 132195 235418 132426 P33571 132651 pPQ171 1111l7 PP1Q44 13414p nppco 16006680 24289Q 131547 24n976 131768 239127 13]08 234Aln 1P40 pp 464 113k17 P1j5i9 NRin700 248431 130q27 246507 11114O 244A657 33147 P40n14 11042 p3509 37pPA PjoARo 1II66720 253937 130334 252011 130939 P20161 13f73p 245P41 91PI4 p1384on 1Ap66 pp4008 131096740 259420 IP9766 2574q4 1PqQ63 9964P 13015 P91315 11nA14 P43A87 13113 Ppa3un i77760 264879 129222 26953 12941P 26100q 1P09q7 196766 130030 203n 10n1 P3degaplusmn5q joq6780 270316 128700 268380 129883 266934 12of61 P62PQ1 lp04A7 p 4 711 13f0l9 P30R1n 114013800 275731 128108 273804 IP8375 P7147 1PPR47 P67603 1P80gq 260007 tpQAoq 949039 IlnI820 281125 127716 27lq 1278R6 27734n 12p85p 27P2l 1PR4N P6516U 12fl165 9502Pun 1lol840 286500 IP7251 28457P 1P7416 PRP713 IP7577 p78350 ip7061 27n819 1p8A63 PSI43 jini77860 292856 126804 289927 1P6063 P2R867 1P7110 P23708 1p7400 P7619 1l161 60618 a46880 297193 126373 2q9P64 165P7 Pq3403 126677 PAQO0q 127A07 p8148plusmn 1P76R7 P67AS 94t04900 302513 125957 3009R3 1P6106 PO8721 tP6PSP pO4153 1p6600 pR67qn 1pp30 27nQ44 916plusmn1 920 307815 1255q5 305885 1P5700 3040p lp5 41 294651 P617q PQp030 1p6700 P7A009 fn5AJA940 313101 125167 311170 1P5307 303O17 1P5444 30403 P5772 po7P24 P6365 281231 297706960 318371 124792 316439 1P4928 314575 15061 3101QS ip5i7 30254P 1P95r4 2pRSSR P7963980 323625 124428 321693 124561 319128 1P461O 315444 p4sectoq 30777f 129958 pq147fi lpAn1s1000 328864 124077 326932 124205 325067 124331 320678 124631 312q46 IP5174 P5 9Aa1
OATw 01307 OArr aPRW
V-INFINITY = 100 KMS
Q = 1 AU G = 3 AU 0 = 5 At 0 = 10 RU G = F0 Atl n r2 AU
T - YRS RAD VEL RAI) VEL PAD VFL RAD VFL PAD VFP RAn VFI
1000 1100 1200 1300 1M00 1500 1600 1700 1800 1900 2000
328864 3t4n5P 38f527 405930 431094 4r6047 480810 509403 529842 554140 578311
124077 IPp474 2P10A9 119878 118810 17P58 117005 116235 115936 I148qq 114315
32693P 390918 37859P 4039q3 42q157 454108 478070 503463 527901 552198 576368
1P4pn 11096 IP1IIR 119q66 1188RR 117928 11706q 116p93 ti5990 11404R 114361
3P507 3lQq 17671q 0P11 427p79 4P2 476089 901580 526n17 f 1 97448P
1P4131 lPP698 12128 1p0O51 118064 117097 117131 1165 11964P 114096 114409
lpn67A 146644 37 0O 397687 42P83n 44777s 47Pr3n 4q7113 5P1943 4 31 56QOq6
104611 2pO7 I114 P0pr6 IIQ147 118162 117PA 1164A7 119767 jI1II1 j 114911
31pg26 JARAfn A644o 3A083I 414941 43ql44 464561 4A0116 51390 y77 r61q9 7
lP0174 10 lip l9tflf ip062p 1104AP 1t8464 1179t 11677 11006 I p5 1147n06
QAR3 lp3IQ7A 4If 3791R iqAq06 4219 R 44ROO 47n311 49a56
6
4601
1An01 104941 22tA7 ItIR4 1pn09 ln02 jlft00q 117196 I1rq96 II AW4 j110I9
2100 602363 113778 60042n ii3Ro 59833 113A61 594nP 113A09 CfR9qq 11414n 6A47A 114909
2200 2300 2400 2500 2600
626307 650151 673901 6q7565 72114
113PS2 112B3 11fV96 111998 111626
624364 64R0 671957 695621 719201
113Nt 1128q 11 0 11030 111696
6P2475 64631 670067 69379 717111
111ra 1Pp2q8 110463 1161 11o168
617qAO 64181A 669=6 680 p2
71PI1
1l14 1jdegPQ0 1142P 1115
11179
6fo0Q71 63A6F04 6742p 6fl6A
70463
1110 l1I6 1lpisq 11097
1ilnq4
Ron2 4109R7
61971 611
6deg4 74
1 10043 1lArN4 1o6l 11
111i
2700 7446559 111277 74P710 il1lfl5 740817 11131 716103 i1199 7PPI23 li1i0 7n7Q79 il1n31 2800 2900 3000 3100
760ql 791461 814767 838014
110950 110642 110352 110078
766146 78Q519l 810821 83606A
1i0O77 110667 110376 110101
764P9P 7R7A2 81nq6 A14171
11103 11n69P 1l09q 110121
7qq7l6 783101 A06404 AP0648
111065 l1791 i14r5 110179
791941 774898 7a1qn 8214pt
11117) iifnn9 j nls 1127
71l n3 745-7 77 717fl ef0 9 9
11413 11116
lfnfl 1099 I
3200 3300 3400
861205 884343 907430
109819 109573 109340
85925A 880396 905483
In9840 ij9593 10939Q
A97163 S8Oro0 p03987
10n961 I19613 Io979
R5PA6 879q71 pqon9R
in9o11 in9661 tq43
A4460 p677PO 890l0q
1ifln3 I0q4q
io9ro7
npnAo 8471A A7MIOM
l1nl9I O0959 00703
3500 3600
930470 953464
I09118 108908
92P523 951516
1n9137 108Q09
q96p6 Q49619
10q199 10804P
qpPfQ2 045084
nQIA lnRQA
q1389 9361
1nQP77 I09nq
8q3lp2 qlO1r
fnnflA3 n06
3700 976415 108707 974467 1087P3 9796Q 10A740 96P0n3 IP779 aq076 10891 AOit I M n
3800 3900
99324 1022194
108515 108332
997376 1020246
108r91 108347
4q9479 1018148
108 46 10816P
q0nq9q 1013R07
1085 4 inslOR
9661 loo99p2
Ri IA464
q6702 9860n7
foqh 4 nQA67
C
lab
C 4000 4100 4200
1045027 1067823 I0Q0584
108156 107Q89 107899
1043078 1065874 1089636
In8171 10W3 107A4
1041179 106l975 10R67A6
108185 I18n17 I17P-S
1036637 109Q43P 108Pi91
InPPf2 InR050 nI7F7
I0lA346 105135 101NR88
l0o894 108111 in7n4
10071n7 Ifl0u40 l1j nI1
0o2847 jOR08
o 4300 4400
1113313 1136009
107674 107526
1111364 1134060
107687 1o753a
1109464 11N216n
107700 107q91
1104qt1 1127613
1f7713 in717Rn
noe61n 113nn
ln77PS I07634
1079910 1nqA1AP
jO7n04
In7776
4500 4600 470o
1158676 115131 1203921
107384 10747 107116
1156726 1179361 1201971
107396 107259 1071P7
1194R26 1177463 lP00071
1n740o in770 I07138
11i0277 117q13 119920
lfl746 1np97 107164
1141990 1164900 118710
In7ua8 lo74A I 07 9
11nn 1144n 1169Q7P
in7t4 l7479 i0711Q
4800 4q00 5000
1226502 1249057 171587
106989 106867 106749
1224551 1247108 1269637
107000 106877 1067Q
1P2652 1249P06 3267736
107010 106P87 106760
I1flAnq IP40693 1P63182
i 7039 I6912 067Q2
1po076A P1i3317 lpSt449
1070 1A1M 106097 1pIl0A
In696 193deg31
1n7n9 l0n 5 In6oO
5100 1294093 106635 1292141 ln6645 1P9024 106654 1289686 106677 1p77349 1l6710 l 0A03 nAnin
5200 1316579 106525 131462r 106935 1312723 106944 1308166 106qA6 2POQRln in66n7 97f4qA In6714 5300 5400
1339034 1361471
106419 106316
1337084 135P521
1064P8 ln635
113518P 1557619
In6437 106334
1330624 111060
In6458 i061q
I32PP7 1344706
0640A 1o613o
1300RPI 133P29
106f n6103
5500 1383887 106217 1381937 106226 138034 106P34 1179479 l06P94 1167117 In6oil 1349670 j6fA 5600 1406282 1061P1 14n0433P 1619 14nP4P9 in6137 139786 InS17 138Q9nA n6103 lIAAnl tnoon7
5700 1428658 10602 1426707 106036 144A04 106044 14PP44 106063 141180 ln6no 13crVnV ln619 5800 5q00
1451014 1473351
105q38 105e09
1449061 1471400
if9945 1o585
1447160 14694q97
1nR3S 109A6S
14429~9 1464q9
io9071 jO98A3
1434P3 14669
i06n05 l09016
1l11gt 1413 04
I60n4 jOnp
6000 1409670 105769 1493720 I0977 14q1916 l09rO 1487P93 1097n7 147A888 Io9pn9fln13 4739
PRW DAP 0130l77 nArr q
V-INFINITY = 200 KMs
0 = I Au 0 = 3 AU = 5 Atl 0 = 10 All 0 = 20 Al n = 52 AU T - YRS PAD VEL PAD VEL vAn VFL RAI VFL iAnVA nAn vri
00 20 40 60
1000 1 005 33546 4575q
1146943 159357 304778 PA0667
30(0 18471 31945 44004
70461q 368R97 3n0006 203263
Onn 17ROA 9fl7P 4273Q
6P8A7P 17q61 11265P PSSns
t0nno 17614 p0177 40nq7p
hA6pe
17g06 P2O363
20Nnn PTq10 3ItR 4lr0
AA7AA 1340n3(40200 11177 P9A3A
cpnnn ) l9A7 o00o9
p0in p11n4 pAIn pA177
0 57225 p66467 S5592q 268242 -410r qn07 q 1 07 P7274) oll6 P74116 6r6A pcqA 100 120 140
68217 78875 89283
P96922 249n89 944688
66499 77137 87534
p28230 25180W 2454CA
651i24 75636 6O0q
pqq06 P5I00Q 246P2Q
603rno 7p774j 830q
261A77 p5171 P477p9
60211 701 7Qqpl
P63t540 6
24966
7l 7n qu AA7r
pt r104 pbni4 915n06
160 180 200 P20 240
Qa497 jo0q554 119481 12929Q 13q023
p404A3 797495 214200 231780 pP97o0
97730 107780 117710 127921 137241
P4114q 217614 P14677 pl21Q2 210061
Q6196 106931 115141 IP5044 139696
4175P Pl81P1 710110 p22968 p301n
q3143 10311p 110067 IP7P tIPfoo
943nn PiOjRn P npl 133361 PI1Of6l
AQ763 0047A
jnlp ]P 7np pA2 c
24U471 P4001
214fl7 p3P2P6
011665 I98PI ll A IA F
lp2pn
pl2AA olfA1 236C61 P14t1 2nA4
260 280 300 320
148667 1524n 167751 177207
pP7R01 226302 224s03 P23634
146883 19645 16596P 179419
2282n9 P6qA4 2P5146 PP363
145PA l4A3 164156 173P04
P8Qo 2P6A04 PPgT37f P24072
I4Inno 19 913 t6In13 17043o
990117 pp7Aq vp9PS7710 P245pp
13771n 1471A 15 o 168s6n
ppnA9 PP0164 96574
16AAU 14A5l tRpol t516116ngp
pIM143 990ftg 29OAm p9Mo5
340 186612 222503 18481A PP2711 183n3 2p2oo1 170Rjp ppflo 175164 2P3no 1718A PU 360 380
jQ5973 205293
221480 2205I
194177 2004q90
221669 PPnTP7
lqpqrA P20IP73
22843 pp02
100155 IOS4 4
22216 nplpn
1043 103670
pP22275 pp172p
t1A069A 1n01n
ppAIf7 ao
400 420
214576 223825
P19701 pt9
21P776 222024
P19A6n 210q06Q
211151 Pn30q
PPO06 pIfl 04
20771A P96ouo
pp0lp2 Ptj4or
PnAl p12062
PP117A3 pl P4
10011 20110
291939 pPni
44o 46o 480
233043 242231 251393
218205 p17542 216928
23124n 240427 249580
P18341 217660 2170145
2PA00 39704 2705
28O66 t17714
P17191
22615n P3r34 24471
1 61 P90036 2i719R
P21A 2303q0 p39450
10136 PtAttn0 P17717
1gt1goo 2pAt P6
loc7p 010-t p10PAJ
900 520 540 560 580 600 620 640
260531 269645 278737 287810 296863 305899 314918 323921
p16357 715824 219326 214860 214422 214o10 213621 213254
258729 26783A 276q2O
286001 299054 30408A 313107 322100
216466 219Q27 215423 P14050 21407 214090 213697 213327
P7187 P6610R P75pAS 284357 q13n0 30P4P 3111t4 32n460
216q67 216021 p2511 215034 P14q86 21416S 213768 213191
Pqlq97 262700 2717pt pAn044 28qAS7 2Qq14 31$TQps 316Qn
2l67A6 P16227 p q704 919219 214797 9143P6 p c90 213530
24854A p5761 26666 A
p7q9 nl pR471A p0371 38270A 1167p
217114 216R34 P25004 P150p9 219njS P14971 210i t
p1317qq
94q9l l519i4 260101 P6onq 27Rn6 P9A60
s55 loP
213 0 P1Amn p1A77 qos plgx73 pi1tnl6 21148 ptdnn
660 680 700 720 740
33290Q 341883 350844 359791 368727
212907 P12579 212267 211970 2116A8
3310q7 340070 349030 357977 36691p
212q76 212644 22232q 212029 211744
529146 31R1A 147177 356p3 369057
213n30 212704 71018 212n8 211706
3P qOn 314f67 34AP1
2P76P 361602
P11176 P1PA0 P12ifl P12202 211000
3P2n63A 30OAtf 93Rqp 347441 196156
213386 PI314 P127o0 IPII
PIP2n6
31X1I7 p10 lp7qp 33S 3434A
PI06 p43n3 p1ogtnpq p19f62 p1pqp
760 780 800 A20 840
377651 386564 395467 404359 413242
pl1419 P11163 210ooa 210684 P10460
375836 384748 391691 402543 411425
211473 211P14 210Q67 210731 210505
374i0 3P9fl2o 3QIq3 10nAA4 4n4766
P11922 211261 211p 210774 PI0947
1706j1 370918 1P841R 30733 406181
P11610 2111AS p1111t p1)RA6q P10637
365p2q 37411S 383033 3010 ufln771
211706 21123 211963 211 21077
js713o 36 Q0A 37U7fl8 3p340A 3QP2
9n57 V1175 2i11)7 211R0 21100
860 880 900 920 940
422116 430981 439837 448685 457526
P10246 210040 OQS43 209653 PO9471
420pq8 420163 43801q 446867 455707
210p89 21OO8 209882 2096q] 209508
41q630 427502 436358 44N05 454044
210120 P10120 p29Olq
lPAQ727 pl-q4p
41sflO 4P300 412763 441607 45fl444
21n416 p1023
1no 2flQ804 p0616
4nq6pn 419476 427316 41615n 444Q~7
pl0ql 21033 PIfllP4 POQQP4 P0QVP
40102PA 4n07o0 41A5 p7 f3o
4360A1
2101 p1n056 p90i3 p101p2
lan096 960
1000
466359 490475185 484003
209295 209126 208964
464540 473365 482184
20331 209161 208997
462876 471701 480519
2fql64 89tp 209027
45P73 4A80o5 476910
pM0439 P0o262 P8904
453704 462607 47141p
pOq47 200169 Pfl9j98
441t9i1 4S3T54 46204
pR3 pfalP 2f075
0A1 011077 PA9W InPnW
= 200 KMSV-NFNTY
T - YRS Q =
RAD 1 AU
VEL G = RAD
3AU VEL
RAn
5AU VEL
0 = 10 AU RA VEL
0 = 20 AU PAD VEL PAn
52 AU VrL
0
1000 1100 1201 1300 1400 1500 1600 1700 1800 190 2000 2100 2200 2300 2400 2500 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 410042400
484003 528001 571857 615593 699224 702765 746226 789616 63294 876212 919431 962603
1005732 1048823 1091877 1134899 1177889 1220852 1263788 13066Q9 1349587 1392454 1435300 1478127 1520936 1563728 1606503 1649264 1692010 1734742 1777461 18201681862863
208964 Pn8231 p07612 207080 06619 206215 205858 pn5541 205256 pn5000 20478 p04556 204363 p041A5 Pn4022 p0371 2n3711 P03601 P(3480 203366 2(3260 p03161 203067 20279 Pn28Q9 Q2817 2n2742 P02672 202605 202541 P02480 202422202367
4R2184 5261A0 570036 613770 657400 700940 744400 787790 931116 874386 917604 96n779 1003904 1046Q94 1090048 1133070 117606n 121Q02P 1261958 130486q 1347797 1390621 143346q 1476296 1slio5 1561897 1604673 1647433 169017q 1732911 1776D 18183371861031
2 n997 208p59 207636 207101 206637 206231 2n5872 05R53 P05268 2n5010 204777 P04565 2n41371 204103 pn40 9 203877 n3737 2036n6 2034q85 2n3371 203264 0116 p03n71 202082 2n2Aqq 202APn 202745 2n2675 02607 P02943 202493 2n242S 2n2360
460911 5P4513 r6366 lnqR
69~7pR 6qqp66 7427P5 7A6113 R2q43q 97P707 ql92r5 q9qq9 I00P224 1045113 108R367 111337 1174574 912733A 6f79
130318ti 1346n73 1930tARi 1411789 1474611 16 74Pn 1560211 160Pq8 1645747 168R492 1731P4 1773Q43 1P1664Q1P85 344
PO9027 208289 Pf765A 70712n Pfl6f654 p06246 205P88 20sq65 Pq9M7 P09npo P04786 204R73 p4378 P041CQQ 20403q p03A83 2n374 205611 P034R80 p0337 P0P6q 0116A p0374 PnPO86 20P009 P02A23 202748 2nP677 202610 PnP46 p0pusra pnP4P7202172
47lt6qlO 920901 564736 608460 652082 699614 730068 78PW1 RP6772 s6Qn7 q1PP51 Q59418 qO8544 1041630 10846A2 1127700 1170685 121164A 125661 IP9q4O 1342376 138R9241 1P4p8 1470910 1511717 1556508 159029P 164P041 16847P6 17P7517 177oPs 1o12Q40195q634
poq0q4 pO894P po77fl6 p07162 P066qn nepR pn9q14 nqol 700301 9fi0I1 pn4805 pn4qqo pn4104 04PI4 OSamp0h8 Po8q5 901754 nW36p n3419 pn33S5 pfl977 P293177 po3nAP pnQ03 Pn2qnq 2(P830 p0975 0P683 p0P616 pn55j Pn2490 P2n43P Pn276
471419 5t63sp 5s9q16q 600851 64644A iaaQ57 731331 77675f 82nn61 563311 Qne195j q406a7 qqp7p fl350q
1O7R9O2 11p1fl1 1164nn 12n7843 jpn770 I2167 133653 117Q411 l P222 1469071 lt(7R74 qqn66 169340 16361s9 16709A 1721663 17646 1n707n 1A4Q761
PnqlqA 6ppa
P0f42q 50rql pn771 5400 pnFY7 sq0QA7 p6748 63A6n4 pnexpq 6070794 pfl50qq 7pflO0 P5631 76P0)
6338 Ant 4P7 p09074 819610
po4RI9 AQ979 Pf467 q389A6 p04t) 081867 PA437 10p4A7 p0407n 1067867 p03o1 1l1nain Pn377 117A p03Alq ltQA641 pn31 l2309V P23nfl 12823 P0310 12=9p
pn3190n 116k066c nl05 Q14i0A
4Q
pn3005 14r366 pnpof 14o6A4fl PnpnR4 1S3aAl p02765 5pnppcl poPQ93 16p4 A 6
202P25 166136 202q60 171nO6 P02409 1527R
Po2P4 17oF4P0 pflpA4 1I3An0
IQA5 pn AzA3 pn71q6pnvq165 2A68 pnlp gtAn43 pOt6M7
6t6 pnq6 P4 o pft At0 pf 4tL 4
pn11AP 201 pn10164 pnonq 9AI A6 pnWU7 n n pOn 90 pnt A
n10
-nR l pn0943 0 pflRAI p(9709 pn712 20P A 43 pn577 pn 9 pn9065 plPlfQ
4300 4400 4500 460n 4700 4800 4900
1905546 194821g 1990881 2033533 2076179 2118809 2161434
202314 202264 202216 P02169 202125 202083 02042
1903714 1946387 1Q8Q44 2031701 2074343 2116977 2159601
202317 20PP66 202218 202271 2n2197 202084 P02n43
1QoP027 1044690 1()P7361 P30013 207P65 221580 2157Q13
2021q p0P6p p02220 P00171 20212n 202(86 20Pn4
18q8316 1q4qS7 10864q 2nP6300 7068q94 211tr74 21542Q
P02313 po2p2 pnPo914 pnP177 pnP133 oOqn PnPn4
89244n IQSo0q 1977767 p00416 P0630n55 P105686 P14307
pNp30 pnpo7q Mp293 Pn2jR3 pi9l9 Pnnoq poPn4
1Rgn76 9Pdeg4AM 2966060 2nMAP6 pf51306 rqO30 2136596
p09345 9990 P0944 pn106 pgt9rl pn9W7 20fl6
0 5000 5100 5200 5300 54O0 5500 5600 5700
2204050 2246658 2289258 P331851 2374436 2417015 499587 2502152
pn2002 P01965 201928 201R93 01859 p1827 pO17q5 201765
220021A 2244826 2287426 2330010 2372604 2416183 2457754 2500319
202004 201966 201930 2o1q5 p1P61 201828 2n17)7 2n1766
2200520 2243137 PP85737 23283 2370015 413493 2456069 P4Q8630
2006 p0106A 21031 201806 p0186P 2(1APQ P0179A 201767
2196814 223Q421 2P8P0(1 2354613 2367107 P40q775 245 346 P2q4I t
Onpnn p01971 P01934 )njgQq 20IRA 2f1A2 p0ISn1 201770
plq0qpi 223359A PP761P3 231A714 P361297 40387 P44644 P24qoq
2001n4 201076 P0lo3q pqjo4 nl 7fl
p0tA37 pninqo pnt74
17nI9 PP1716 2264301 36878 234Q4A P3qOflIA 2ampa7n 4771P
PnnO 01087 pflloOQ P2n14 pfl1i9 p0I046 Pn104 p017A3
5800 5900
2544711 2587264
201736 701707
P942878 2585431
201717 201708
941189 2981742
20173A 2nt70Q
2537469 2580022
pn1740 01712
23156P 2974111
pn745 P01716
PSin6fA PS6pna
pm17r3 Pnj9 4
6000 2629811 201680 2627978 201681 2626288 p2168P 2622q6 9164 96166q57 068A P604741 9nIA6
fATP Olin0 nAr 11PRW
V-NFINITY = 300 KMS
4 11U0 AU 0 5AU 0=10 AU 0=20 AU 52 All T - YRS PAD VEL PAD VFL PAn VFL pn VrL otn Vrr ovn Vr)
00 1000 1165378 3nn0 AP5491 sn 66607P 1flOnnn RI7 IP pnnnn UPP244 Connn Papfn7
20 21796 4140fl7 20477 4PO3 10734 4P415f8 rORq a3It54 prp 9 Iinflh6 r~n ~nA
40 38036 369657 36966 372106 3rrp1 374090 34340 176 6P0Qr 172A72 5nPS3 AllAA13
60 53147 351260 516P 392663 90l63 113770 4P70n I9e7Q 4n08 AtvIpq 68A3 i3a 104
80 6769q 340803 6S6142 14l1797 6499 14Pr31 APunR9 14317q 62117 144107 761Rl INAnu3 100 Ftt00 314 191 8033 331L47Q3 70070O 51 76n73 tI62n 7r7l II6n R~n7 IIIp 120 99886 129309 942P97 3qp~ 33n17 33nr65 qCln707 q300l7 RQ10A I159o q7flAn 19on7 140 109694 325844 jOAO04 3P6212 1SnA77 3PAq17 104403 3gp7f77 n40 3P7qgt 1n0ArC 3An02
16n IP337P 3P3081 12176c 3P379 1P0453 IP3W0 t18085 jp4f76 1I5R5A 3P4192 Ipn1 I91506 18n 136947 V0867 139334 3p1108 1A34n1 3p100 131903 lp1688 1P0170 4pn1 13P7S 3t1r57 200 19043q 31909P 14A821 319p9P 1474R 110021 14rni0 o1074n 144A nnA 45n1 3In16 220 163862 117534 16224n 3177n4 180oq 11714A 5A4n7 1A1A 1 7pn 311844 157nn IA 91 240 260
177226 190541
516P46 1335138
179601 188QtA
31632 1192A9
1714P94 1A76
316 lq 3153I72
171714 R150
3167M qt~7A
1689 317n2 IP23j(6F 319~1fI
17n 310n1I 3 isrl9A111
280 201813 314174 20218P 3148r6 p0nqp 141PQ 1qpgqo I iAp nq3n 114777 1n906 I1if7 300 217047 13328 219414 31347 214092 I13 11 P11469 1367p Pf449 313866 Pnpnnnl 3IIan0
32) 230247 31257q 22161P 312668 PP7P47 1074P 9PIA47 AI2886 p9 15 6c 113n6o 9P07TA 3YIll 140 24341A 311912 24178P 3ll0 t P40411 312098 pl770Q 1171A8 P34669 31pI(7 23471 39IIfnq
360 256563 311313 2949PS 3113114 25355(1 311t4st PqfQ97 Tj1A p47749 111708 74AP4 11111A 380 26q684 310772 268044 310836 26667n I08ol P64n3p t1rlA 26n80 31113 innoI 31l707 401 282783 310PA1 28114P 10340 P70766 310390 P771y7 31nellqt p7PRA 1nr1n 97101 v1nAnQ 420 205863 309834 294221 i0pP8 2CfA4P 3f0033 2001854 I10n3 pA6RAO 110136 01461P 16 440 30A924 1094P4 307281 309474 09001 3n016 303P24 If0R90 pqofQl7 f07fl 9074 4 n173 l 46n 32197n 3109048 320326 IA0QO04 MjA041 A00133 31660 in0A209 11pQ1q 3fl03fl Jjfl9O0 I009 -l
480 335000 i087n1 33355 3n8743 33197t 3nf770 32QP28 i0Aqn 3pr0f7 n804n lpAn 3rkan8 -j1
500 348016 3083A0 346370 in8419 344qA5 3nR493 4PPQ6 30AqIA 33A8qn OAfn2 31q6 n70 CD 520 361019 3080R2 350373 nA110 9T7ff 30pirn 19qPot m0ApII 3s1860 3nAon 140S0 30034
540 560
374010 386900
1078n5 307546
37236 38534P
37835 307578
37n075 383q93
3n7A6p 10760
36AP74 381246
flx7oo 307659
361$A84 377777
3f70o0
077p8 161400 17a0qn
IVAnM7 307 o
580 3q0959 307305 398311 3n7334 306920 307160 30u2A0 07410 Ko07p 3ff747r 3A1141 qn7quA 600 412919 307078 41127n 3071M06 400878 A7130 407162 in7j77 4f3A9A 307piq 3q0001 9fmni 620 429869 306A69 42422n 3n6802 4PPA27 106014 4P0107 30609R utA5A6 o7o16 4 19 1 1 Ininoo 640 43R811 106669 437161 3n6600 419767 3n6711 433043 067R3 4P09n7 3n6qnn 4m6ni 38080 660 451744 3064176 450094 3n6500 44A600 n06R20 449 71 Ine6q9 444pt 306811 43410 At8A71
680 464670 3n6298 46301Q 3063P0 4A16P4 In63Q 4588P i0o676 49932 06496 4512 101103 700 477589 306129 47-937 3n6150 474941 10616A 4710r In6203 46823n n8o99 364np86 720 740
400500 50340
905069 105818
488848 501751
0lqRg 3n5837
4A7451 5003n
A6n6 3n5891
4A4713 4q7613
3n6040 inq5A5
4R11P8 40401r
IOnOS Anop7
147r887 4A068n
In1IR jm n00
760 516304 305674 51465P 305692 52393 3n97n7 910 0A fn738 8rA0Q 3n577 9q4Q1 nS00R 780 529197 105537 527544 3n5994 qP6149 3nr60 5P3307 n5 O to077R n3c86 -Iqni 3nm0q RO 542084 3n5406 540431 3n5423 930n31 3n5437 53A81 3n54A4 53p69p 3n55n rpIlln 3tqM$ 820 840
554066 567843
3n528 305163
553313 56619n
3n5pq8 305178
991013 5A478
3n9311 3M91C01
r4016n 56p033
3nq337 n5916
9452P1 998388
09373 3050s
940017 917
30SulR 3f 04
860 880
580715 5q3583
305050 304q41
570061 591q28
305064 304Q95
577660 ffl26
30507A 314066
974qnp 987766
Tnq1nn if490f
970P47 P41n
30i33 3f90nl
69P6 570132
3 n9q5 30nAp
Q00 606446 304837 604791 3n4050 6n388 fltA6t 60deg0826 in4AA4 9q96q 30UQ QPtPf 304n 920 619304 304737 61764q 30N4750 616P46 04761 613UR2 34712 6nq6n4 I0R1I 6n40p7 311q8 940 960 980
632159 649009 657856
3n4642 304550 304462
630504 643394 656200
304654 304562 304471
62OIOO 641q50 654796
304664 304972 304483
6P6334 63Q1P 602026
n046R5 104liql ft4501
622640 634n 648 3PA
3047 304818 304-27
6117P4 63091Q 6411I
n41q 3n4054 1Ane6p
1000 670699 304377 669043 304388 667639 30I497 664867 A04415 66116P I04440 65616 3n474
nATF 011077 PArr 12PRW
V-INFINITY = 300 KMS
0 = 1 AU 3 AU 0 t vjAU 0 =1I) 0 = 2nOAP All RU
T - YRS RAO VEL RAD VEL RAn VFL RAD VFL PAn VEt An Vrl
1000 110n 120n
670699 7341165 79997
904377
3039q7 303619
6690q3 73320A 797300
304398 30406 I03696
66763 731101 7c589A2
3fl419q7 I04014 I03649
664867 7Q0pp 7Q1fl
Ift44195 A46q fl1fl
661162 79PRQ 78cflSn
104140 mn4nnn Inpl
6RA1nfA 2nou 783941-
Af474 rftn~q
I140
1300 1400 1500 1600 1700
86298R 926965 990897 1054788 1lL864
303407 103173 902970 302791 30263
86132c 925306 989237
1053128 1116984
303414 3n317q 302Q79 3027q5 302636
P5Q0O Q1896 q7826 101716 1119971
103410 303184 I027Q A027qQ 30269q
857Pq q100 qqRnP6 104913 1112764
3ll4fll AnI10 3 9NqR7 nfnn6 30n646
89 X ql79l7 QoII 104900Q 1j00939
0144q 3onN7 Iflpoo 30Pq16 3065
847l 0116r6 q7-4A7 1030259 110o16
304A6 IftN5 1016 90p29 Inq
1800 1q00
11R2468 1246264
3024q0302363
118080 1244604
3O244 3n2367
117qq4 1243t10
30P4o7 30p6Q
1176585 120377
30P03 inPI75
1170741 12369PA
30211 3npipp
1l6A 7 13nQ
I n9Ifl9
2000 2100
1310035 1373783
30224q 302145
1308374 137212P
3n225 302147
1306q5 1370706
np254 902150
1304145 1167AQ0
30n22pq I0 54
13flflR 1164n5
n2566 in2160
1904191 13570
3096 3091l
2200 1417510 302050 143594A 302oS2 14341933 30205t 14131614 A3oPn5q 14p7740 Ano64 1Jdegl5l 3n07
2300 2400
1501218 1564908
90Iq63 n1884
149q556 1563246
31066 3NA8n6
1499t40 156lnpq
301o67 3n1887
14Q5320 15a0A
301071 inIACl
14Q1410 isSlPl
101n76 AnIn06
14F10A 14A4P
nlnA4 inn10n
Un
25-00 2600 2700 200 2900 3000 t00
162A589 1692241 1759887 181 Q519 183140 1946750 P010349
101811f 30174 I0167) 301621 301566 301515 301467
162600 16n057q 1754224 1817857 1881477 194q087 200A0A6
I0lpp l 169sol 3n1744 16PQ16P In1681 l7qP07 301622 1816439 30I68 1oAR00Q 301516 1943669 9n146Q Pn7P67
I0I124 I0174A In1682 0624 ois6q 30191A An1470
16P2600 16A637 I74nn61 181361P 1n77PI3 194nAICQ P004437
In1817 In1748 ln1695 in1626 Nolq7 in0If In147
i6i87AA 16AP441 1746nn 1Pnq7n7 IP7A3 106P7 P005pl
I0102I1l6lP4fl nlr3 167An0 o16Wn 179n7np
301630 l8N301 3n1q74 1A6A0n 9n19p3 lqjn4 7
n1475 Ia10i
Ift~ 0S 0 nt0
3n 65 301635 301~0 30nhI A 0it 17q
3200 3300
p073939 P137518
n01422 3013n0
2072279 2135855
n1424 3n1381
2070n57 P13437
In145 0j8
P06806 21316A5
in147 n0 13 4
20641n6 912765
01p 9nliP7
2n76n P12lA0
I 1fh414 9nI1 0
3400 3500
2201090 2264654
301340 A01303
2190427 2262990
I01341 301304
PlqRfl0R P261571
3014P If013l
2195175 2298738
in1944 301306
21012c5 2254810
n1146 30tinq
PlaA709 P421
3fl13 90
3600 2328209 301267 2326546 01268 2325127 301260 P22PqI 3N12P1 I3IR36901573 P1117061 n 6
3700 3800 3900
2391758 2455300 2518835
301234 3n1202 3n1172
23q00q4 2453636 2517171
301235 301P03 301172
P198675 4P216 P915751
in1p2q 101203 I01173
28840 P44qI31 2512n15
301297 i01905 901174
P381008 P44S446 P08q7A
90l39 nln7 3n1176
P375315 P3D030 P2O5q6
Inlo4p nn sl0 301t q
4000 2592364 301143 80700 301144 2570200 301144 2576443 301146 2572504 I01147 56986R in110
4100 2645886 301116 2644223 3n1116 2642803 I01117 263Q965 301110 P636P4 901120 p6p037 301153
4200 4300 4400
270q404 2772916 283642
301089 301065 301041
2707740 27712)2 2834758
301fl0 3n1069 301041
27n692n 76q9j1 283333R
901OQI I01066 10104P
P70342 2769Q03 PA304qq
Inl0QP In1067 3n1043
PAQQF30 91690n4 P2A655
l01no3 untceR I01044
26Q9877 975 g975 Pl0A06
1o06 In107i 9nl047
4500 4600
289c924 296342
301018 3009q6
2898260 2961757
301flQ 30oqo7
28q6840 P6ni37
i0jO11 9n30097
Po40o01 P57407
i01000 InOqR
PA80059 9O5394A
30i021 nolno
gAn33R7 PQ46819l
3ntnI4 Nnlfnp
4700 4800 4900 5000 5100
3026914 3090403 3153887 3217367 3280844
300975 300q55 300q36 300918 300900
3025290 308873A 315P223 3219703 327Q179
300q76 300956 300937 300q18 3n0on
IOA829 3087328 3150o0P 32142P 327798
900076 30056 ln037 30Ooq In0c0I
3gp qAa 3084477 147961 3P11441 3974Q17
nOa7 innq07 00q9 900lq i00nP
3017n3n 908ln5p5 1junon 3p074AA 9P7n96n
90079l 9nno5 3n0a9
300lot 3n90n9
3010n12P 9nT7Q
9137p79 99fl740 99609n
9fnnnl Rnn6 98nn t 380QP9 3fntn
5200 5300
3344317 3407786
300183 300866
3342652 3406121
InO83 300867
3341231 9404700
300084 100867
3930Aq 3401~qR
f00nA4 300A86
134439 I9Q7qQ
30flAS 9mA6q
9927671 A991131
nnn7 90n71
5400 5500
3471252 3534714
00851 300815
346q07 3533090
300i51 300636
3460166 I91162q
900851 300A36
946324 3528716
m00852 14613611 90037 91P4PR
i00n 3 nnAA
3q4490q 351A0ll9
0nnqRS Ifnel q
5600 3508174 300821 359650q 3008219n5l088 n0n21 359P49 0009 358g289 9n0493 R8140A 300095
5700 3661630 300807 3659966 30080 3658R44 AnOQn7 36aq7ni In0A08 165173 9000q 1644Q41 A0nflo
5800 5900
3725084 37A8534
300793 30070
3723419 3786970
3n0793 300790
372lqq 37P5448
300719 90070
371I914 318P604
3fl0704 f7pi
9715190 9flm7ns
l377 jq639 00789 370tIN 6 ift0906 1771859 RfnRi
6000 385198 300767 3850318 300767 9840896 100767 384609P 9007F 984086 0076Q 9835jP 30n77(l
PRW MATP 1111171 OA r 13
V-INFINITY 400 KMS
0 1 AU 0 AJ f = 5 AU 0 = 10 Atl 0 = P0 All m T go Ai
T - YRS RAD VEL RAD VFL PAn VFL PAn VrL oA VFl otn Vrl
00 1000 1340775 30nn s66844 rnnn 717Z11 10000 9808AN 2nnnn 4Q8711 sonOn hancnl
20 24236 482917 2305n 4A67qq t2(41 4Ap041 P26ro (48l26 P7i 47371P 9a 111 4 I 40 43647 447040 4P320 44939n 41469 90121 416t7 ar131 4P467 (440laq 6 Ql t11atp
60 62188 434201 60821 43430 r 69 435474 9R619 a16 AICIO 91o 44iofl 74fnol0 10AA
80 80316 426721 78q92 4gt7177 77qP0 427q16 7646n UPR2p9 7A2nq 4P8111 8724 4490
100 120
98201 119922
421981 418695
q6793 114504
4P22Q2 418021
9579A 11440
4PPq6 41nnQ
0416Q iii71
UPPP06 uj0173
a347 jt1171n
p1n6q 1Q1
toP4A IInn
41111 41ntoIA
140 160 180
133527 151049 168493
416278 414423 412093
13P101 14061P 167056
41641 4j4qqQ 413063
1103 148931 169065
841691P 414663 413147
120on0 146741 1641AI
II6A0 1aAQ
4101
ipPOtA 14920 I e540
416065 414nA4 1411
134 14Af 166nl1
16o7 4 g=4 41ftlt
200 189886 411758 184449 411840 181148 41101Q 19111a olpo 17n191 g2910lft9Ij07 220 24n
203234 22nr44
410768 409933
201790 21QOQ7
4l0O04 4n9QQA
2nnA6 p1TnRq
u(100 41O04A
108A80 PIAA
411nnq i1 I115
1 7nn P142P2
u1tin3 1100p3
lonlI vj70a
u1oonA 1011 o
260 237822 409219 23617P 4n9p79 23qp60 4n0110 P1116 4n0109 2 401 400470 99gtq6 U0nf06
280 300
255072 272298
408602 408064
253620 27085
408651 4881n6
PqP904 260729
4n8AAA 408l4n
29nq64 P6777p
0A7 uoglnP
P4Pr7 p6131
40nqpq 40OA1
4M P601114
a0shyunfi
32n 28502 407580 28804 4n76P7 PA6026 0n7656 p4Q06 4n77n pAP76 4n7769 Ppac (AP
340 360
30668A 323898
407167 406740
309230 3P40n
4n72n1 406R 1
3n4105 3PIP7
4f7P25 406n4q
10PI12 31QPAR
4077 4n6Ap7
30ngn 317139
4n7115 i6nv3
ponA 3167ql
40t00
Mrt601
380 341012 406452 3309( 406u79 31AP45 406901 36431 4699q 394244 n6gol 33395 4OrAt 400 358151 406145 356693 40617n 399163 4061 0 35361 un6194 3513Q7 66nr7 noSo7 420 375281 405867 373821 4n5S9 372680 40007 17n6n on9q3 v60441 n9075 36740 L4qnnn 440 3923Q8 405613 300937 415613 3A004 4f9$ 387780 an967I 1A(n091 I 14 1fA Ulflt928 460 400506 4053110 40A044 4n9109 406000 15414 u04888 on9441 40P6n06 ao5t71 4n 3ql up RatqpP -
480 426603 405169 425141 4n5183 4P4ffl 4n5197 421070 fl012 4J0671 anonfl 41 9APni ftn4 7 500 520
443692 460774
404q68 404789
44223n 450310
404q84 44800
4deg102 4rA171
4049q7 Uf4A1P
43qn6l 456136
ao5np0 4483
436741 498flIn
4sSrn46 In4095
413F2 45I11
4nflA=n bIeAI oW
540 560
477847 494914
(04619 404496
476383 493450
4O46PQ 4n4470
475944 unplOq
404640 4041180
473pn4 400266
(04660 Uo44 A
470093 4870n1
naAAN 1n49p0
4601PO 4pAnn
40o00 404917
580 51I75 404300 9t0510 4n4321 9n361 404331 507NPI On4Rh 50404 (n41AR 5n0O2 poundn14 8
60n 5P902q 404171 527564 4n4182 SP612 4n4191 5p437y 4L4pn7 9P7I00j 40L9P7 ant3 620 546078 4040n4 54461P 404052 911460 104160 94 141c 41b611001f793flltl 936nn08 4fsI0 640 563121 40391q 561699 403qP0 960911 4n3037 59499 4fQr2 56012 4n3060 9RIAOP 4n1o04 660 580160 403A05 578603 4n38t4 177R49 403AP 979400 un3839 9706 401n9v 97nA7 4n0AA 680 700 720
57194 614223 631240
403697 403505 403498
505727 612756 620781
403706 403605 4n19n6
9949AP 611611 rPOA5
403711 40361n 4ntq11
9qp9tp 604146 62656A
aon376 416P2 u1094
rnnfn 6071oq 61iA
4n141 403637 4n01q
R09t An4757 Ap111
4 0199 4nitn1
MN992 740 648270 403407 64680P 4n3414 649695 40342n 439A6 Un1411 64112n hn3a44 63n666 fn1u98
760 780 800
665288 682302 609312
403320 403237 403159
661810 60833 697844
403327 403p44 403166
66267P 679686 6Q6606
413133 4n3290 4n1171
6n601 677612 6q4620
1n1141 403260 4nl3180
6 5n10 67514n 692141
40l396 ii07P 4ni10o
65qA2n A7974 61095q
tjOk3q 4A3o84 gnRAL4
820 716320 403084 714851 403091 713702 403096 7116P5 (403109 70013Q on3119 7n64nt 4010v7
840 733324 403013 731859 4n3019 730706 4030124 78627 40303 7261I3 403043 724 tfl3l4
860 750326 40245 748856 402Qr1 747707 4 2455 7496P7 40PQ63 7431P8 4fl071 74n3Ps uf4Otnb
880 900
767324 784320
4n2880 402818
765859 782890
402885 4n2823
764705 781700
4OPpgo 402127
76P63 770617
40AC8 402839
760110 7771nP
uOPon7 unPnU4
75136 774P87
4AfIfl 40094
920 801314 402758 799844 402763 79AAQ3 40P767 796608 it0n774 7q403Q 400783 7q1717 4AfIP73
940 818305 402701 816834 02706 15684 402710 A13Ro7 4n2717 811078 4n2728 80A1fl7 40P3 960 835293 402646 833823 402651 83P672 402655 830884 40P661 828090 40266 Rq1A6 4126Q 980 852279 40254 850809 402598 840658 402602 847569 02608 S45030 402616 84204 402695 1000 869264 402543 867793 402548 866642 402551 864551 402597 6fPO a 4n265 85009 4P9I73
PRA WA1033077 PAGr 14
V-INFINTTY = 400 KMS
0 = 1 AU 0 = 3 AU 0 = 5 AU 0 = 10 AU 0 00 At) (3 252 AU T - YRS RAO VEL RAD VEL RAO VEL PAO VEL PAD VE PAO VFPI
1000 869264 402543 867793 402948 866642 402951 864951 40l2M7 86P018 40p6s Rs03 aflq3
1100 1200 1300 1400 1500 1600 1700 1800
954159 103003 1123814 1208593 t293346 1378075 1462784 1547474
402318 402129 401969 401831 401711 401606 401513 401431
95P684 1037531 112341 1207121 1291873 137660P 1461310 1946000
402321 402132 40171 40133 4n1713 4A160R 401515 401432
q9153l 1016377 11211A6 lPrQf59 1200717 1379449 1460153 194494P
402924 402134 40Q173 4013q 40171= 40160Q 401916 401433
94q45 1034P76 1110002 120oI57 128R606 137313p 1498037 154P724
40P29 40219q 4l077 41100 U01717 401612 4n118 401435
q46RA1 1fl1706 111649q 1pOP6 1PR6000 1370716 l4q44 19400q
40p39 40P144 4010AI 40t4 4017P2 401619 401521 401417
Q41794 102941 It116 19947 19A1911 1167167 14r510q 193A41q
411094 4Ptq91 n~l47 401047 401I76 401IIQ 4P91 4ftI441
1900 2000 2100
1632147 1716806 I001451
401357 401290 401229
1630671 1715331 1799976
4013ql 4012 1 401210
162 154 1714173 17q817
401159 40pq 40131
1627309 171pnsp 1796695
401360 002 q2 4n I1PP
1624758 1709nAn0 70447
401163 40125 40t14
l6pin0g 7056n 17Q0p7
40166 4f1 oR 4n1117
2200 2300 2400
1886084 1070706 2055318
401174 401124 401078
188460q 1960231 053843
4n1175 4n1125 4f107
1AP1490 IsRn7i P90683
401 76 40112s 40070
18813P6 2q9q47 P050557
4n1177 unI1P7 4fn0l0
1877 IQAIPR9 PA478q6
4n1179 fl1jq
4flnRP
287UR66 lq4Ki P04ilnl0
4n1101 4f110 40InA4
2500 2600 2700
213q920 2224514 230Q100
4n1035 4n0906 400959
2138449 2223039 2307624
401036 40Oqq6 400960
P1370P5 PPP170 P236464
401036 400q7 400Q60
2119158 Ptq790 P304335
Un01037 40nqnn uo0Q61
Pj3P43 Ppl7 04 P01664
4flInO 4009o 4006l9
PlpM60 P-19A4 Po758
4AonUT inlnnl 4nn004
2800 2900
2393678 247A250
40M025 400894
23q2201 2476774
4000q6 4008Q4
239104 P479613
400926 408O9S
2388q91 247 4 3
4nlOQ7 4008q6
P386P9 470n06
4n0oa 40oqQ7
2IR9PRO P466 1
4nlnn 4000o0
3000 3100 3200 3300 3400 3500 3600
P562815 2647374 2731928 2816476 P9o3Og 985558 3070092
400864 400837 400811 400787 400764 400742 400722
256133q 2645898 273049P 2815000 2890543 298408P 3068616
400865 400817 400P11 400797 4007A4 400743 4n07
2560178 P64437 272qPqo 2813P3A P89A8t 2Qq220 3067454
40O6q 40083P 40081P 40087 4n0764 400743 400722
255F047 P642605 277rn 2911709 Pq6PA 2qR0786 3n651lq
400866 4nflPn8 40 W1P 4O07nR 40076q 4f0743 u007PI
255361 400867 P9116 963Qql 4o0nQq P63c0IQ
747414flfAlj P7Pnqo p0nQi Q 40fl0789 poaoo1 PSQ6fl 4 A0766PRQ0 Po7AfQA 4A0744 2q740 062627 4n0M74 30sOqri
4fnAR 40nno4jshyuonnl4 4fn00 0 afnnA7 40t0kc ampAn74
3700 3154622 400702 3153146 4n0703 319193 400703 314qn4n 40n079 114719R 400704 914067 4nn 3800 3900
3239148 1323670
400684 400667
3237671 332q14
400614 400667
3P3650Q 1031
40068r 400667
3p34 74 3318806
400689 40n668
IP31670 316109
4006P6 4n0668
250f 3311000
4ftn87 4nnA
44000 3408189 4f0690 3406719 400650 3405550 40069 14n314 4100651 94fl07 5 O65i 656 4nnAg
M 4100 420n 4300
31492704 5577216 3661725
400634 400620 400605
34q1227 357573n 366024A
400635 4006P0 400609
3490065 3974577 365Q86
40063q 400620 400606
3487928 397p440 3656948
n0695 4n06P0 4006n6
14R92p0 56q79n 9654P46
4n0696 348l1(I 40n062196A9609 4nn606 169noi
4nnA7 4ftnA9 4nnn7
4400 45O0 4600
3746231 3830734 3915234
4005q2 400579 400566
3744754 382q257 3913758
40059q 400570 400566
374391 3828094 3o1P799
4005Q9 4ffl70 400966
3741454 3AP597 391047
unnr59p 4fln07Q anO767
171R751 382292 l97751
Un0503 4n0580 4Anse6
3714907 9N0On 03lap
4nng l 4nnFno 400W68
Pgt 4700 4800 4900
39qq732 4084228 4168721
400554 400543 400532
39q8256 4082751 4167244
400554 400S43 440512
300Q793 4081588 4166081
400n54 400O43 40053P
39Q40r5 407q44q 41634P
400999 400543 Lonl52
IQQPP4 407674P 4161214
4059 400q44 4nnl0l
93AA0 9 4q7Pq5q 41544
4ftflR6 4nn44 4fnq3
5000 4253212 400521 4251739 4005P1 4250972 400921 4248432 4n09P2 4245773 40fl9 4D415 R 4fn091 5100 4337700 400511 4336229 4n0511 4339060 00911 413021 400912 4330211 4001 4326nq 4n0512 5200 5300
4422187 4506671
400501 400492
4420710 4505194
400501 4n049P
041q947 4504031
400502 40n4gP
4417U07 45011
40fn2 ao0402
4414606 44q017Q
40050 40qhiQ3
44jA40Q 449406A
4f0t09 40fi93
5400 4591154 400483 4580677 4004A3 45A14 400481 4986173 iflfnl3 ssO9661 40044 4-7044N 4W4
5500 5600
4675635 4760114
400474 400466
4674158 4758636
4n0474 400466
467pqq4 47q7471
400474 400466
4670854 479911
400479 40n466
466814n 4756 8
4n0479 40466
466917 474890
4nnilS 4nA7
5700 4844591 400458 4843114 400495 4A41Q5f 400458 4R3qnog 4nN48 4A3704 40049q 4A89861 4flngQ
5800 4929066 400490 4927580 400490 49P6425 4049n 4Q24284 oI00n40 4921569 4nn4 4I7111 4nnrsI1 5900 5013540 40042 5012063 4n0442 901nq9 40044 5005758 4nN443 5006049 40n443 9001800 4n0443 6000 5098012 400435 50q6535 4n0435 53Q9$71 4n0439 5093230 4onu495 s4qo1 04(1415 5086A7 4nn416
PRW 0ATF 011077 pAr 15
V-NFINITY 500 KMS
T - YRS 0
RAO 1 AU
VEL 0 =
PAD 3 AU
VEL 0 =
PAn 5 All
VFI A PAn
1n AUl VEL
0 = pAf
20 All VEt RAO
02 AU Vrl
00
20 1000
27095 14P2764 961678
o300n 2604A
qo7po RAU417
non P V5R
77772P t65173
1n000 pqn5R
i177A 964461
nn0nn i0poi
rn0n Ssqno4
r9nnn A-
qo n0o on 16
40
60
an 100
S0041 72315 94283 116073
34281 235Q61 1518477 15059
411870 71111 0cs0A0 114816
9An6q 5P43S7 918716 51510
4A176 7n133 9P941
11100
939q64 5P46Pn r1AP70 S 93
47q77 6n408k 01147 11706
FJQ0a6 qp44 -9tclfl1 1Of
4q314 70014 0114Sp 1jP4PP
9477n 9P471n 51010 5155R41
67An R94117
ln1o9m9 lpnPnq
90rlt 9~tfnA 9 rl4ft
120 137746 912710 136500 qt2 8V3 13641 51201U jt14173 rtfl4 137374r 53n004 t3Af0t C5i9=06
160 180864 f0971R 607 5n9781 17787P7 g it 17771 fl005 - 17641n Sflafi 1PO49o 9nft 180 200 220 240 260
20P344 223786 2451C7 266581 287943
5fl8603 507866 1)07194 90661P 506124
2010AI 22252 24303n 26531P 286671
9118747 9n7011 qf7221 5n6643 5n61r1
PnOIQ6 pp1A20 P43o3 264411 PQc76A
g7F8 5n704p q07P48 g06666 5n6171
tg8ln PPAPIQ v141603 P6P0AU PA41fl7
nR8S n70fj 9n7p0 1 PrmAn 506209
1Q775f P10071 p4n3Ao Pfl21684 8p2q7A
q0A8AO r0ArnA4 tn7i7 cn6i1 56931
Pni11 VP17n 4PUI P614P9 IRJAfn
q0p-v90 9nA7nlq 9ngtl rn66A01 5AAl
280 300 320 340 360 380
300287 3301614 351926 373226 394514 4157)3
$i057q4 5n5338 505016 504731 504477 qn4249
508019 329340 350651 371950 39323 41at5l
5fl57P7 qn5359 n5s35
904748 5n44q2 5n4p62
1fl7ff7 1Rln tq770 371036 Aop39 41r5qA
RO9744 5fl57i 0R048 904790 n4511P qnq4pp
In9614 326047 34AP47 360519 3n0814 41pnS4
mn577P t505AQ8 05n6q rn477A Ao419q s(42A7
30429An 3p5SVA 34670n 36A058 38031in 410556
905q5 In5asp1 no0qno g T4708 gn4c37 9n4in3
3n=119 lpAlft9 147171 301A49 30401 41n n
9M91V7 nnn nl=qn2
qnn3 90495 At4inA
40f) 420
437062 498323
504045 53856
435784 457044
5n4095 c03867
434A69 496124
9n464 5fl3t7
43034 440qq
gn4f7R eo3P8A
41706 41 in11
904 50nn0l
4Alf16F 4RP79A
Ffftlf4 fvnw4
440 460 480 500 520
479577 500824 522064 54399 564528
9036A6 q03530 503387 50525 903113
478297 4Q9941 50783 54P018 563p47
-503606 n339 qn33q5 0n3263 9n31n
477376 4qA621 939n6n 45In4 693pp
qn3703 rn3546 rnf 1 0 ofl36A r0314c5
47R4A 4070A6 518P2 5301 r6f776
tn715 Cfl3 7 rn11t 1 n3lp7l
C014
474P6n 40949c 167nq 931
q5al3
gn17p7 5fn36A
n398 Rn316o
47IA64 mnt3n 401107r mnl5p RoaAAMIA0j flrgf6 921 9 a2 0 5Ffl3A5 qniAA
940 560 580 600
585753 606973 62188 640400
rn3Oo i02q15 902816 5027P5
584471 609690 626009 648117
5n3097 902)21 502Ap2 5n2730
r8lq45 604764 62078 6471A9
00ft3 50202q 5n21P6 clP734
581006 603911 6244PI 645631
Mftno 02l 3 9f02P3 nP71t
9ASn141 611194A 6pP74T 64011
n3n4 I6nPi4no1 nWot
9n2-4
5704o1f 6 0 6p1791 64A9A
nflnl3 0 n046 5n1006 n5fIqp
620 640 660 680 700 720 740 760
670608 691812 713013 734211 755406 776599 797788 818975
502635 502558 5024A2 502411 502343 502279 902219 502162
66032u 690529 711720 732q27 754129 775314 79650A 8176911
512644 902963 5112497 5n2415 502347 502283 5f2p23 50216S
66 r6 6Aq600 710n00 731007 751lat 7741 3 70597P PI$7Q
qn2A47 502966 rinpilq 50p2418 c025fn Rf22R6 qf225 C021A
66636A Ann37 700215 710431 7516P3 77PP13 740flO0 R19185
n965 =0PR72 on040 =f943 -n9q9 5OPol F22pl0 rnP172
66 n 6863q 7079P6 7pS714 7oRQO 771083 7026U gl44
526rI IfnPq78 9pns 01420 Knp560 502006 r023 FnPi76
A610 68r191 7nAp27 7p-301 74qrn 76oeD$ 70n80
1iOU4
o009t Cl9sfl3 5nP9n6 q5111 5091n sntn0 5n9I9 5nA Pfl
780 800 820
840160 861343 882523
502107 502056 502006
838975 860057 88123A
502111 5112059 5f2000
83704 P9Q12 A90305
c02113 rn2061 K02011
83616rR RT754q 8787P7
502117 nfl5 qOP015
89u690 AR57q6 s76Q6o
Kno1p9 n2n6q So2Iq
83nRnfl A94918cP A753K7
100n19 qnfl 9n0no3
840 860 880 900
903702 92487c 946053 967226
501a5q 90t1i5 50172 501831
902416 92359P 944767 969941
501962 501ot7 5011 7 4 501P33
Q002I4 OP265q 943834 (69f006
501064 01c1 501876 50135
8QqqP4 02107q 0422nP 9634P3
50I16 q01093 Knfln7q fOIAIA
Rq141 ot01311 n4n0480 961647
n17P n10P6 R1p03 oI 44P
9649 Ql611 q3A771 95qonq
80l10 5 5fl 0 1010A6 9f1our
920 940 960
988397 1000567 1030735
901792 501754 501718
987111 1008210 1029448
5017q4 t01797 501721
9A6177 1007146 1121514
50176 017158
501722
0945Q3 1005761 1026928
If17n9 sn1761 9f017P5
Q8211 100 347 7 1025140
q0I102 901764 n172P
081046 100p1 102313
Ifvs A177 5A11
980 1000
1051902 1073067
501684 501651
1050619 1071780
501686 501653
1049680 1070845
501687 501694
1048093 1069257
901600 so16q7
104630P 1067461
01603 901699
1f4b4g 1069504
qfIKa6 If1A62
9ATF 033077 DArr 16PRW
V-INFINITY = 500 KMS
Q = 1 AU 0 = 3 AU 0 plusmn 5 AU 0 = 10 AU 0 = 20 All n = S2 AU
T - YRS RAD VEL PAD VEL RAn VEL PAD VFL PAD VFL PAD Vri
IDO0 1100 1200 1300 1400 1500 1600 1700 1800
1073067 1178874 1284652 L390406 1496140 1601856 1707556 1813243 1918918
901651 501503 q01379 501274 501184 901106 901038 900978 900924
10717R 1177586 1283364 1389117 1494851 1600566 1706267 1811954 1917628
501653 5n1504 S01381 9n1276 501186 5fl1107 511039 sn0o7n 500Q24
1070n45 1176650 1282427 13RRt0 1493911 1500628 170912A 1810t14 1416680
rO026 501506 S158P Sf1P7S 501186 s91108 50103Q 508e70 5n0029
1060q57 1175058 IP808911 136982 14qP312 159An25 1703723 100407 lq9OA
rnfl69t7 S fllflA f13I 0127 g1Iflg qoIlq q01040
nIq08 gs0QP6
1067461 172qo 1p7qOn 13P 474C 149n47n 19q617qs 170186$A 1054g 101321P
90 nt6Aqlft6 rt 4 sn1s10 91712T4 Sl1AS P76046 nI1R0 11s8e61 SnItRg 14Po2A7 n1110 l5gqQ17
501nI4 16qo5q 0OfqRl lAn lOt gnip7 Iq0nRp9
9fl1Ap nq71 50188 gn1oAp sf1i1 5n1112 cflln43 gn n o0 5fnnlo
1900 2000 2100 2200 2300
2024583 2130237 2235883 2341521 2447152
500876 900832 r007Q3 500757 r00725
20232Q9 2120947 2214593 2340231 244586
5f0R76 5f0833 gn07q3 9O07q8 90075
PO0P353 218007 PP33659 233q2gO P444021
500877 gflOfP3 I90-q4
079P 0fl7
P220743 212636 2P22040 P937677 441 07
snA77 FO0R14 F0l74 K0f7RI r0n726
P01807n 212 5gI Pin15 957Q9 2441418
5088A7A qffA14 Kdegf70 g0050 Ko0A
201A446 7IPfl4 pp777 P13pat 741AAR 7
5nnq nfnn
degnfn6 sfn6A 9nn7
h
2400 2900 2600 2700 2800 2900 3000 3100 3200 3300 3400 3500 3600 3700 3800 3900 4000 4100 4200 4300 4400 4500 4600 4700 4800 4900 5000
55777 2698395 P764008 2869619 297218 5086816 3186410 32q20o0 3397587 3503170 3608750 3714327 381c901 3925472 4031041 4136607 4242171 4347733 4453293 4558851 4664406 4769961 4675513 4Q81063 5086613 5192160 5i297706
rs10695 900667 5fl0642 500618 9005Q6 5n0576 900557 9n0539 q00922 500506 500401 500477 500464 9900492 500440 900429 900418 q00408 9n0398 500389 500380 9n0372 500364 900356 500349 900342 500335
2S514A8 2657104 27602717 2868324 2973n27 3070525 3189119 3290700 3396296 350187q 3607498 3713035 381860q 3924181 402q74) 4139316 4240880 4346441 4452001 455759q 4663115 476866) 4874221 4979772 5085321 5190868 5296414
50o0095 500667 5n064 900618 90056 qn0576 5g0l957 50093q 500522 500596 5n0492 507 5004646 500492 50044n0 5004 q 50a418 500408 50l038 5OAR9 500380 50037 900364 50n056 500149 5n034P 5n0335
Prtcs P696161 741779 P867982 247PO25 t078RB 3184177 3P29767 x305353 390fl36 16n6516 3712003 R17667 370PP38 40206 4134173 4P3q37 43454q 4451098 4596616 4662171 4767725 87327A
4478828 50P4377 5gqQ2p5 9P5471
SnrAqq q00668 90064P 0f1618 5n0q6 nfl76 500 597 900l q 500522 q00907 90049P g00478 500465 SfO0Sp 51044n 9n042q 90041A 50408 50019R 500980 00980
90017P 500364 509(05650O340 500342 50033-5i
P94AQIn P694947 2760150 2865766 47167 3l176q69 S1Al2558 3PR814R 31q37434f9316 36048F6 371047p 3816049 q021616 4027185 413P79n 4p3R1 434I876 4440435 4954C)P 466nF34 4766102 4A7164 4q7P04 5082793 91883n0 fi3846
50nQ6 5547090 g00668 96P6s9 FO64 796 rn061q PR69O66 Rn50507 P6046 rnnrl76 n7906i 50n57 9iRn65t 50nn9q 2P6P4n r(nfln3 i5q1Sp5nn907 3q74n6 nfln4 f60qA4 80479 370P n0469 3814111 On459 lq107nn qnN440 40P5P67 5ffnlpq 130890 5004l18 4P3A30n qNdeg4fl8 4341455 fnln09Q0 4447914 5n0 ) 455 070 sqf3R3 4650628 fn07P7 476417 5n0Oa4 4g60nThP q0nl~6 4075278 fn94q nnp6 5n142 5186373 s5lq3 OtqiP
(06A6 PS4nu4A rnn668 p6qnnl
fl64 75567 qn0A1Q PR61Pra snnoQ7 P06ARa gnfl77 3n70144
nnq58 317non 90fl4fl O8A57 s(0523 llp3 9 nA 9(1fMt5 44710
5(0it4p 360o207 7 8A 7 05 9
r00465 3811414 5lf45 1IA0S075 nn441 U0234
i0nOQ 412Pn0nl qnfl4lq 4P9646 5004A18 43Q OQ 5efl0Qg 44447-0 5n(Oxq 4gRnmn qnnAt 465caq4 007 U761M6 5nn64 46Aq4i1 50nx56 075A4n5 ndegfl49 c7nP nO34P 91P197n 50n395 9PRlln
srns$7 rnnA6q qnlnu9 5nnO gnoncnA qnnR7 90n0nshyRnsfnt go n9 Onnrnfl7 0
g0nn03 snonI
q
fnniAg onnu53
qnnil6 0n0itl
5fnlnrlq 5n014nq tfl030 q
5n~nfO 5nnl 5002 snnjes 5fnln07 rnn14q 50M04P 50n839
5100 5200
5403251 5508794
500328 500322
5401959 5507502
9003P8 900322
540I015 S001PR R506r5P 900322
53qq0 5504933
qn0i9g nn0pn
K9q7469 530O
50nnxpQ 900322
59464q 550n187
3n9 5nn39
5300 5400
5614336 5719877
500316 900310
5613044 5718589
500316 500310
5612100 5717641
r00316 500310
r610479 5716016
g50n16 nn2n
W0R549 r714n85
5n0316 qnOxAl1
q6n07l4 5711PAn
5nn116 Fnn 11
5500 5600 5700 5800 5)00 6000
5829416 5930955 6036492 614P028 6247563 6353098
rn0304 50029 5002q4 50028q 500284 500279
5824124 5920663 6035200 6140736 6246271 6351805
90035 5n0p9 090q4 500289 5n024 500270
rA 9lA1 59P8720 6n0i4Pqi 613979P 649p7 6350861
500305 g0olqQo RnOq4 500280 50OP4 90027Q
21555 0pflo S826in 6138166 649701 614q239
500309 581q624 Knn2gQqp AP R)1PQ04 03l6qR qonPq 6136234 50P24 624176R qnn07q 69473nP
50Minr 5002OQ 50nnq4 5O0Aq 50n094 qon507Q
R167n4 qOp Ip 6nP7A1 61I39i 6P38994 6340U4q4
5nnxnK srn Q gn09Q4 500n0q nnf04
gnnon
PRW flr 03W77 nArr 7
V-INFINITY = 600 KMS
T - YRS 0=
RAn 1AU
VEL q =
RAr) 3 AU
VEL n =
PAn 5 AU
Vft n = 10
PA) Atl
VFL a = PAn
20 MI VEL PAMn
5p fU VVl
00 1000 146oQfo 300f 0754n7 rnnn51 4r4A 1nonn 713o0q 0nnnn 6AanAn sPnrn F9t-no -20 30269 647005 29354 648417 2A~4 64004t pfln 04486 313u1 F4Pn R SPnol AIo4 4nl 60
56979 83199
6P5413 617524
55061 8110l
695863 617714 A1477
A61246324q76 A17P00 807 o 0
APA17 AInO
F56o A14l1
6pov7q 617AAe
7r Qt11171
61nnpQ 615RA7
80 100
10910( 134926
61340l 610860
10A043 133R4q
613R2 610047
lo7177 1st3e1
61361 11flnn
tOAgqo 1502c
A1Po n67or 611AI3940611non
e137n i155 13 flW s
AlAq0 AinIft
120 140
160656 186325
609134 607884
15057P 185236
60q2n5607Q30
1S8872 jAlrp7
600opg07aA0
157O014 IPI1r7
6flQO 008113
J-1N IRinfn
n031 6n0S6
Ierl 14Ut
6mnn An7017
160 180
211940 237538
606q36 6n6103
210895 236441
6n6072 6n6p2
Pjn130 PA5710
6n60q5 6n6940
rnnoo P34654
A7nn O9Apt
20A467 p 43Q30
A7nq1 606P7
11fn PAn I
AnSnSn AnAfl
200 263099 605594 261990 609617 P6173 o5rW 9Ann8 Anc66 pr03A 6056 P6deg10PI AncrtQ 220 240
28A637 314157
605101 604688
28753f 31305
6n510 6047n5
P6n05 619131 1193I6fl4
2897n0 i 6
65103 An311206
p4tr5 n-ins
6n9168 An4746
5nptSn A
-tpo Anq1 n AA0471
260 339660 604337 338559 6n413r 31751iq A0461 336604 6nt95 -4 7 An148 39 5R An-4Ao 280 300 32n 340
365150 3Q0628 416096 441554
6n4036 603773 6n3543 603330
364044 389521 41407 440445
6n4048 603784 603592 613348
363031 388780 41P4t5
UIQ0f
6n4nti f 61370 6n3590
An315A
3876A7 414j31n 43q41U
A1u1AOtq Aen 60n60 A1A62
IAJ61o R866P4
u1pnrq u37T 4 a
6n4n8 6fl1I 6ndeg9 A370
16un 3A611 41I-Afln
41in1
AnflnAA Anfnlp sMIn 71 6n3A
360 467005 603158 46580 6n3165 4A5151 603170 4fA37qA7 6rfjl1A A6Pqnc An32A 4ATl7 n Aa
380 492448 6n2095 49133A 603002 gfnql 6030A6 4RA04p3 n113 4AP9p fAnInn 4n 9n An1 1 400 517885 602848 916774 6n2Rq4 510An27 A62n8n 514A94 A0PA5 t37v An2871 5I o An9 420 543316 6n2719 542204 6027P1 91111456 6n272Z 940979 An P70 r3044 611P716 ri3 npi Anr76 440 460 480
568742 594162 619579
602594 6024A3 602382
56762P 5P3o5 618466
6n29q 6n2408 6n2386
566p8f 9inf deg17719
6112603 6fn2qj6n2980
966qq 5011j9616P7
Anp6np 6P406 AnPQI
R645n 58o53 e135i
An2613
69Rn9109
R65hn qnoA=IA
6fn9613 Annl 6m Q
o 500 520
644991 67039q
602P88 61 22Nt
643R77 66q0R2
e0P2QP 6n22n9
641126 66A533
A6p295 6129oA
641035 6673140
A62paq AnP1
64degnr 666145
612311 6npois
Aqnq4n 6egna
An1 An1 7
-J 0
540 69r804 602121 6 4 60 0 6nPi29 6303417 SnpypV 6qhl An931 Aq1537 A1P1I4 6o119n 6- 191A 560 58n
721206 746605
60207 601)77
720092 749412
602050 6O10O
71031R 744736
6npn0p 601ORP
71140 743S35
60n15 Anlpq
7164P7 74P31
A9nq 69t1A0
716455 74 17I
6nn6n 6nlno
600 772001 60IQ12 770885 6n1915 77n31 601017 76gP8 An0 767600 An10o 76711R APOM1 620 640
707394 822784
601851 601704
79627A 82166q
601A54 6n17q7
705p4 n2024
61n186 611708
7q4 p07fl7
n 6I0t85q Anln01
70368 lP46
601n61 A1n14
7qP4k7 ct77
6118nl 60inn
660 680
84173 873559
601741 6016q0
847057 872441
6n1743 6n1692
A4Ao AviAv
6n1745 6016qu
A49n 870477
Af1747 An1A06
A4314U pAQP99
snstyn 601AO
A4lll 86R451
An19i 6 17n0
700 598Q43 601643 87827 6P1645 807071 6IA46 A0q8Q A016Aa 804500 68160A 0917A7 6n1Aqp 720 924325 601597 923200 6n15sQ9 Op452 no1601 P12P4 AnlAn3 q q07 AnA19 01015 61An6 740 760
949706 975004
601559 601514
948580 97096A
60197 601516
9u7983 Q73plO
601558 AnlIr17
046618 071)09
6n11560 An 191 a
45147 07071n
6nlq6 611spl
040MA4A6158 Q68nn finICD3
7)30 1000461 601476 999344 601478 Qq8597 6fn1470 0q737 6014I1 oqAOqo 6014A qqRQ 6111140 800 1025837 601440 1024720 611441 10P362 6f8144P 102P744 A01444 lp146ln A01446 102047 Aflfta7 820 840
1051210 1076583
601405 601372
1050091 1075466
6n1406 6n1373
ln4335 1074707
6nln7 0n1374
1048116 1073487
n14nq tnuARPn An1W76 107105
An1411 611177
10481c7 I071157
Af1012 Aflt1A
860 880
1101954 1127324
601340 601310
1100837 1126206
601342 601311
130007A 11Pq447
601141 6131P
10857 1124PP5
6n1144 6n1314
loq7961ll22q2A
601146 6n1 tq
IQA4A 1121838
An14 eniI7
900 920
1152692 1178060
6012R1 601254
1151579 117694P
6012R3 601255
1150A81 1176183
60128p3 6n1256
1j4q 3 11749qq
6nIP9 60157
11P n 1173653
6IPA6 60158
1147176 117P9916
An1 4 6019 0
940 960
1203426 1228791
601227 601202
1202308 1227673
601228 601203
12019q 12P6013
601P20 60lpo4
12003P4 122i60
601231 An6p125
xo001 12p4376
601039 6n1006
11QT899 1P21t5
6n1943 61nl9
980 1254155 601178 1253037 601179 1252277 6001180 1251051 A0f11 1 1240736 6011R2 1240519 601183 1000 1279518 601154 1278400 601155 1277640 01156 1276413 601157 1p70q6 6011RA 127181 An1O
PRW DATF 011077 PArr Is
V-TNFINITY =600 KMS
S=1 AU Q = 3 AU Q - 5 AU 0 = 10 AU 0 = 20 AU a 52 AU T - YRS RAD VEL RAO VEL RAD VEL RAO VFL An VEL Olin VL
1000 1279518 601154 1278400 6n11SS IP77640 6811S6 IP76411 A0e11S7 1P7580 6nII di IP7A87A fin116O 1100 1406320 6n1050 1409201 14n4441 140PI0 14WA 6n t nf4 f I6n10 I fip10nP fintftv 8 140MS71 ot$ 1200 1533102 600964 1531483 6n0964 193IP21 600K6 1920s~q Afl0n llP864n 6000fi6 I~SPOMA AnnOA 1300 165Q866 6n0890 1658747 6n0891 1697999 600891 1696790 6inARQ2 1655400 6008ql 16wAq n 600A61 1400 1786617 6n08P7 1785497 6n08PA 17A4739 finOAPA 17A349A 60048 179214P 6n0npq 178n64A 6f)OAN 1500 1913355 600772 191P3S 6n0773 101147P 6n077 la10P33 Afl0774 10OA871 AnM774 tOO0T11 Aftoft 1600 2040082 600724 203896P 6n07P9 Pn39199 600pq Pnl6Q$4 Aqn7P9 P03 5I 6n176 P014011 finnvo 1700 P166800 600682 216568n 6n0692 P1fi4417 6n0683 P161679 A003 P160P 600693 P1606A 6AnAA4R 1900 2293510 600644 229P389 6n0645 Ppq166 60deg064 P4fnl83 An0649 PPS9nn6 6n0646 PPA79Qq 60nOA8 1900 2420212 600611 24190q1 600611 P418127 60o061t] P410pl A6006 1 I7P 60ft6lP P t4007 6nn 20o00 2546907 600980 254786 6n0qRl 94rQPP 600981 2941777 6009A| P 4I$ QI 6nn-R1 P9400 6nnq p 2100 2673596 600553 2672479 6n0953 P671711 6n093 P67fl46r Ann5l P66q077 6n0Aqq P6673c ls 6n 0 -q 2200 2800280 600528 279915Q 6nlO9PA 27Q6394 6n00PR 78 T147 Annqps P79o57q 6nl09Pg P~q4011 Annql
2400 3053632 600484 3052911 6n0484 30n91746 6n0484 l0fin4QA AiNn44 304010- AnnPS 104710 AftW 2900 3180302 600469 317q1ni 6n0469 1179416 6P046i5 3177167 60fn465 31776q 6noM469 17Nqvl 6nAlA6 2600 3306969 600447 3309846 6n0447 lln n] 6n044 33n183 Ann447 l300441 6n0 44 Al0Wl 6AM44 2700 3433630 6n0410 343o5nA 6n0411 A411743 6n0431 14304ql 6n04ll X4Pqnqi 6n-nAol 14PIP67 6Mnl 2800 3560289 600419 3559167 6n0419 19940P 6nnulq 3597191 Ann416 iq-q74A 6nfn416 is19in Annh16 2c)00 3686944 600401 3685821 6n04n1 36Arin97 6An4nl 368l06 Ann0n01 6AP4ni 6nn4ni1 69n9RP 6nnaop 30-00 3813597 600388 3812476 600i g IR11710 6nnARP 3stn40 Anl03PA 3PoqOiP 6fl0ARq An I01 6 n R shy3100 394n247 600175 393q126 6n0379 3918136n Afl037 3Q37108 Ann3759 T0 67 in3tqqo A n6 shy3200 4066895 6n0363 4065773 6n0i64 4069n07 6n0164 4n63799 6nn364 406P34A 6nnIA4 406m4Aq AnnMmA 4 3300 41g3940 6 00192 4192ulP 6n0353 41q1652 6n0193 419n4no 6n-nlq3 418PqAQ 60nlql 4I871 n fion l Cgt 3400 4320183 6n0342 431Q061 600147 411 95 6n0142 4117n4l 60034P u319611 6nMlu 41117A 6ftnl l 3500 4446824 6n0332 4449i70 600332 44Q36 600133 44416A3 6n0lll 444PP7 6innil 401A 6nnl l 3600 4573462 600323 4572341 6n0123 457t975 6n0121 4-i70321 fi0n03 49fiAgo 6noiP4 4r6AQQA 6mqI0 3700 4700099 6n0314 469R97A 6n0115 46Q9211 An0319 46gfi9Rf AnnII 4699ri41 6nO19 4fqNAOI0 Aftt 15 3800 4826739 6n0106 4829613 6n0306 USP4A46 6n0 0O6 482lqg3 An0WM6 UAP0177 An0IO7 4APnPUq 6nnmn7 3900 4953368 600298 4992246 6n0298 4q91480 A007qq4 Q90226 An04g Uq4PRnn 6nn0Q 404AR74 finnoaq 4000 5080000 600291 507887A 6n0291 n7811p 60091 5076857 An0p t qn943n 60nQt q071400 Annio1 4100 5206630 600284 920950A 6n0P84 Pn474P An0P94 5PO14R7 60nPA4 9pnPO0 6nnI84 900nlll Ann A4 4200 5333259 600277 5332137 600p77 9111371 6n0777 513nI16 60$0P77 3PA6Q6 Anfti77 qlA744 Fnni 8 4300 5459886 600P71 5458769 6n0271 9497998 6nnP71 9456743 6n0p71 r491PI 60ngt71 qKlArfinK ndegoV 1 4400 5586513 600269 5985391 6n0269 9qA4624 60DP6r Sr31An 600PA5 q58194A AnO61K qq7QqA- 6nnAc 4S00 5713138 600P59 571P016 6n0299 r71IP4q 60059 870Q04 O60n~qq $7A577 6nn q -i7nf6nu 6inn-Q 4600 5839761 6n0P53 583863q 6n0293 qA37871 600P3 536617 f0npqi qRj9Iqf 6n09 9PIPPI 6nn o~ 4704 5966364 600248 59)6 1262 60024a 5Q644995 6nnP4S 9503P30 Annp p qO6IRIA An0gt4A qQ9nA4A AnA 4A 480o 6093005 600243 6091881 6n0243 6n91116 6nnP43 6089A6n AnnP4q3 6nA37 66nP4 6na4R6 6nno4N 4900 6219625 600238 621R501 6nn238 6pi7717 60nP3P 6pt6461 6lOnplA Aplqnq 6nno x8 API 071 AftnOle 5000 6346245 600233 6345121 6n0213 6144$6 600P31 614310O 600P11 614167R 6nnoll Al3n6AA fitn0ll 5t00 6472863 6002P8 6471741 6n0228 647nq74 600P2A 646o71A fi00PPS f468Ql 600PQ A46Aino 600g
S 5200 6599481 600224 6998358 6n02P4 6rQ7591l 60024 69q6339 6nnPP4 Ati40na 6noP04 fi9Q9011 Ann4 530 707 606724979 6n0P20 6724P08 60npp0 672PQ91 6nnP 0 67Plr 6n0nln0 671n l~ Aftdegni9 5400 6852713 600216 68q159n 6n02t6 6A9n824 60016 694q567 A00P16 6A4914n 6nn0gt16 6n4At Ann 16 5500 6979327 60023P 697820r 6n02t2 607743A 600pip 6Q76181 6nnP12 -6q7475i4 6n0OgtIP 607p74A 6nplp
2 5600 7105941 600208 7104819 6n0208 71g409P 6no n8 71nP709 AnfnPnA 71n136A 6nnpnR 7nQ0j9A 6ftnoAR 4 - 5700 7232555 6n0204 723143P 6n0n4 7P3066t 6n0p04 7p2 QnA 60npn4 7PP7Q n 60flp05 7r 6Anln
Ir 5800 7359167 600201 7358049 6fl001 71q7P7A 600701 7356021 6nnpni 71949qgt 6nMint 199rPf 6nqgtA082 5900 7485779 6n0197 7484656 6n0ign 7483A89 finnlqA 749263P fin0nI R 7491201 6no|a 7470|A 6n~nlqn
S 6000 7612390 6n0194 7611267 600104 76|A900 6n0194 760OP43 A0njQ4 76n7814 fi0n1o4 76n971) Annin4
r PUBLICATION 77-70