AAP-5 Mission Profile 671010

8/4/2019 AAP-5 Mission Profile 671010

http://slidepdf.com/reader/full/aap-5-mission-profile-671010 1/44

05952-H262-RO-00

N A T I O N A L A E R O N A U T I C S A N D S P A C E A D M I N I S T R A T I O N

MSC INTERNAL NOTE NO. 67-FM-114• d j L ' I - \ % r \ i Q r -i t

-'^iaiyf D g j j (

10 August 1967

PRELIMINARY REFERENCE MISSION

PROFILE F OR APOLLO APPLICATIONS

MISSION AAP-5

T e c h n i c a l L i b r a r y , B e i i c o m m

By Mission Design Section

TRW Systems Group

...VV'.V.V.'.V..v.-.v.v.

M SC Task Monitor;

C. T. Osgood

; V . ( N A S A - T M - X - 7 2 2 2 4 ) P R E L I M I N A R Y B E F E B E N C EI-'.-! M I S S I O N P R O F I L E F O B A P O L L O A P P L I C A T I O N S;X ; M I S S I O N A A P - 5 ( N A S A ) 4 2 p

N75-72077

Onclas

00/98 17459

MISSION PLANNING AND ANALYSIS DIVISION

M A N N E D S P A C E C R A F T C E N T E RHOUSTON, T E X A S



05952-H262-RO-00

W

MSC INTERNAL NOTE NO.67-FM-114

P R E L I M I N A R Y R E F E R E N C E M I S S I O N P R O F I L E F O R

A P O L L O A P P L I C A T I O N S M I S S I O N A A P - 5

10 AUGUST 1967

MISSION PLANNING AN D ANALYSIS DIVISIONNATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MANNED SPACECRAFT CENTERHOUSTON, TEXAS

NAS 9-4810

Prepared by

R . L. PettyF . W . Knopf

Approved by ty -ji

/jffiL. C. Lineberry, Chief' Rendezvous AnalysisBr

Approve

NASA/MSC

/ C - - - -

W/vM *•* ^

Analysis Branch

J. P. Mayer, ChiefMission Planningand

Analysis DivisionNASA/MSC

Approved by

; Rj.fC. Petersburg ManagerSpaceflight OperationsDepartment

TR W Systems Group

Approved by

R. W. Jojnnson, Manager

Mission Design and

Analysis, MTCP

TRW Systems Group



Page Intentionally Left Blank



CONTENTS

Page

1. INTRODUCTION 1

2. NOMINAL MISSION DESCRIPTION

3. MISSION ANALYSIS 7

3. 1 Launch Window 7

3. 2 CSM-Active Rendezvous 8

3. 3 CSM/OWS Cluster Combination Coast 9

3. 4 CSM Deorbit and Entry 9

4. POTENTIAL PROBLEMAREAS 11

4. 1 Launch Vehicle Performance 11

4. 2 Height (NH) Maneuver Schedule Conflict 11

REFERENCES 35

111



TABLES

Page

1. AAP-5 Performance and Payload Summary 13

2. MSFN Stations and Capabilities 14

3. AAP-5 Maneuver Table 15

4. Orbital Elements Following the Nominal AAP-5Maneuvers 16

5. AAP-5 SPS and SM-RCS Propellant Budget ,. . . . 20



ILLUSTRATIONS

Page

1. AAP-5/OWS Cluster Configuration 25

2. Preliminary Launch Window for the AAP-5 Mission 26

3. Recovery Opportunities in the West Atlantic Recovery

Zone 27

4. Major Event Timeline/CSM-Active Rendezvous 28

5. Earth Ground Track/CSM-Active Rendezvous 29

6. CSM/OWS Cluster Relative Motion During the CSM-Active

Rendezvous . 30

7. Relative Range and Range Rate/CSM-Active

Rendezvous f 32

8. Orbital Geometry/CSM-Active Rendezvous 34

VI1



NOMENCLATURE

AAP Apollo Applications Program

ATM Apollo Telescope Mount . '' "

CM Command Module

CMC Command Module Computer . . • • . . ' .

C M G Control Moment Gyros, . . .

CSM Command Service Module .

DKI Docking Initiation ,

ECS Environmental Control System.

EPS Electric Power Supply

GET Ground Elapsed Time . ...

G M T Greenwich Mean,Time . , . • • ' . • . -

H ~ Hydrogen . • -. . , , ; .

IMU Inertial Measurement Unit

LiOH Lithium Hydroxide • . .

LM Lunar Module

M Apsis Number (= 1. 0 at First Apogee)

MDA Multiple Docking Adapter

MSFN Manned Space Flight Network ^

N, Nitrogen£ *

N A S A National Aeronautics and Space Administration

N C 1 Spacecraft Phase Adjustment Maneuver

N C C Spacecraft Corrective Combination Maneuver

N H Spacecraft Height Maneuver

NPC Spacecraft Plane Change Maneuver

N S R Spacecraft Coelliptic Maneuver

IX:



NOMENCLATURE (Continued)

O ^ Oxygen ' ' . - - - '

OWS Orbital Workshop

RCS Reaction Control System

RTCC Real Time Computer Complex

S-IB First Stage of Uprated Saturn I Launch Vehicle

S-IVB Second Stage of Uprated Saturn I Launch Vehicle

SCS Stabilization and Control Subsystem

SLA Spacecraft LM Adapter

SM Service Module

SPS Service Propulsion System

TPI Terminal Phase Initiation Maneuver

TPF Terminal Phase Finalization Maneuver

UHF Ultra High Frequency

VHF Very High Frequency

AV Velocity Increment

deg degree

fps feet per second

ft foot

hr hour

Ib pound

min minute

n mi nautical mile

sec second



1. INTRODUCTION

The preliminary reference mission profile described in this docu-

ment is designed for a manned-configured spacecraft on Apollo Applications

Mission AAP-5. This mission will consist of a revisit and reactivation of

the low inclination (28. 87 degrees) cluster consisting of the OWS/MDA and

LM-ATM. The configuration after CSM docking is illustrated in Figure 1.

This cluster will have been in orbit approximately 231 days at the time of

the AAP-5 launch. Insertion of the spacecraft into the 81- by 120-nautical

mile orbit will be accomplished by an Uprated Saturn I launch vehicle.

The AAP-3 CSM spacecraft weight data were used in the generation

of this document. The fuel loading was changed to reflect maximum fuel

required for the dispersed case (Table 5).

The second section of this report presents a description of the AAP-5

mission as it is conceived at the present time, while the third section pre-

sents the reasoning behind some of the decisions made in choosing this

mission plan. The final section presents several potential problem areas

associated with the mission as it is presented in this document.



2. NOMINAL MISSION DESCRIPTION

For simulation purposes, the AAP-5 launch was assumed to occur

on 4 September 1969, at 20 hours and 56 minutes Greenwich Mean Time

(GMT) (3:56 p.m. Eastern Standard Time). The date and time of launch

were chosen due to certain launch window and lighting considerations to be

discussed in Section 3. 1. The launch was assumed to occur from Launch

Complex 34 at Cape Kennedy, Florida.

The spacecraft will separate from the S-IVB and, in the first 7 hours

o f the mission, perform an M = 4 rendezvous with the low inclination

cluster which has been left in orbit from the previous AAP missions. The

OWS will originally be inserted into a 260-nautical mile circular orbit.

After the OWS passivation is performed the vehicle will be in a 257- by270-nautical mile orbit (Reference 4). Due to orbital decay, the cluster

will, at the time of rendezvous, be in an orbit characterized by an apogee

altitude of 254 nautical miles and a perigee altitude of 241 nautical miles.

The rendezvous plan presented in this document requires six thrusting

maneuvers and approximately 6-1/2 hours for completion. These maneu-

vers, the apsis number on which they are performed, the approximate

velocity increment required, and the corresponding spacecraft ground

elapsed time are presented below.

*Apsis (M) Approximate GET

Maneuver Number AV (fps) (hr:min:sec)

Height (NH) 1.5 212 1:38:25

Phasing (NCI) 2.0 134 2:23:38

Corrective combination ( N C C ) 2 .75 5 3:29:09

Coelliptic (NSR) 3.0 134 3:55:27

Terminal phase initiation(TPI) 20 5:02:18

Terminal phase finalization(TPF) 22 5:38:43

Ground elapsed time at mid-point of burn.

3



The height (NH) maneuver occurs one revolution or approximately

89 minutes after CSM insertion. This interval gives ample time and

opportunity for CSM orbit determination by the MSFN network before the

NH maneuver is scheduled to occur. The 212. 5-foot per second maneuver

is initiated while the CSM is in contact with the Merrit t Island-and Grand

Bahama stations and will require an SPS burn duration of approximately

12. 7 seconds. The 45-minute interval between the height maneuver and

the phasing (NCI) maneuver provides approximately 24 minutes of tracking

or update support. This coverage should provide the Real Time Computer

Complex (RTCC) with accurate data for the NCI maneuver as well as .

means for an update of the command module computer (CMC) over the

Redstone ship approximately 12 minutes before the maneuver is to occur.,

The nominal velocity increment and SPS burn time for this maneuver are

134.4 feet per second and 7. 8 seconds, respectively. There will be no

MSFN coverage of the burn itself. The third maneuver in the rendezvous

plan is a corrective combination (NCC) maneuver which will occur-approx-

imately 1 hour and 8 minutes after the NCI maneuver. The NCC, in

conjunction with the coelliptic (NSR) maneuver, eliminates any differences

between the planes of the two orbits and corrects any phasing or. height

error which might be present at this time. Tracking by the Carnarvon,

Hawaii, and continental United States tracking stations will provide infor-

mation for a two-impulse NCC-NSR solution in time for a CMCupdate

over the Antigua tracking station. The CSM will be in contact with the

Ascension tracking station at the time of the maneuver. The nominal

NCC maneuver will consist of a 4. 6-foot per second velocity increment

and will be performed by a 13. 2-second SM-RCS burn. The NSR maneu-

ver will occur 23 minutes or slightly over 90 degrees from the NCC maneu-

ver. This 134. 5-foot per second maneuver is designed to place the CSM

in a coelliptic orbit, 10 nautical miles below the OWScluster. The

maneuver is accomplished by a 7. 7-second SPS burn and will be covered

by the Tananarive station and the Redstone tracking ship. After coasting

1 hour and 7 minutes in this coelliptic orbit, the CSMwill perform the

terminal phase initiation (TPI) maneuver. Again, very good tracking is

available between the NSR and TPI maneuvers, but no coverage is available

during the TPI maneuver approximately 11 minutes after entering darkness.



Terminal phase finalization (TPF), or final braking, will begin soon after

loss of contact with the Tananarive station; the crew should be ready to

receive the final go-ahead for docking by the time they are over the Guam,

Mercury Ship, or Hawaii tracking sites.

The remainder of the mission will consist of crew experiments while

the CSM is docked with the OWScluster. No attempt will be made to

describe or simulate this portion of the mission due to the lack of defini-

tion at the present time.

The mission will be terminated by the splashdown of the command

module (CM) in the West Atlantic recovery zone. The time of the splash-

down will depend upon the length of the mission flown. At present,

missions of approximately 1-month and Z-month duration are being con-

sidered.

Pertinent data relating to the AA P-5 mission and, specifically, the

CSM-active rendezvous are presented in the tables and figures following

Section 4.



page interi



3. MISSION ANALYSIS

3.1 LAUNCH WINDOW

The preliminary launch window presented in Figure 2 is based on a

254- by 241-nautical mile orbit with an inclination of 28. 87 degrees. This

orbit was obtained by propagating the OWS cluster to the time of AAP-5

lift-off. Because of the inability to accurately predict the OWS cluster

orbit, the launch window data presented in Figure 2 should be regarded as

representative only, subject to pre-mission and real-time updating.

A minimum of 2 weeks between AAP-3 splashdown and AAP-5 launch

is presently considered to be adequate. This interval would dictate an

AAP-5 launch no earlier than on the 21Oth day after the lift-off of the

OWS. Two other constraints must also be taken into consideration when

choosing the launch date and time of launch. First, it is preferable that

the launch should occur no later in the day than 21:00 GMT (4:00 p.m.

local standard time at Cape Kennedy). This is to allow for daylight recov-

ery in the Atlantic in the case of a suborbital abort. The second consid-

eration is that a daylight splashdown in the West Atlantic recovery zone is

desired at the conclusion of the mission. Figure 3 presents the, range of

times in which deorbit from the OWS orbit into the West Atlantic recovery

zone is possible for a range of days after OWS lift-off. If splashdown isdesired between 6:00 a. m. and 5:00 p. m. local standard time, the figure

illustrates that daylight recovery is possible from 225 to 257 and from

270 to 302 days after OWS lift-off. At this time, mission durations of

25-30 days and 55-60 days are being considered. Depending upon which

length of mission is finally selected, it is desirable that splashdown occur

in one or the other of the above daylight recovery intervals. For this to be

possible, the AAP-5 launch should occur in the interval between 210 and

232 days after OWS launch. The launch opportunity which occurs on the231st day after OWSlift-off was chosen. This was the first opportunity to

occur in this interval of days which required a lift-off time before 4:00 p.m.,

thus satisfying the daylight abort recovery constraint. The interval between

AAP-3 lift-off and AAP-5 lift-off will be approximately 93 days, while the

interval between AAP-3 splashdown and AAP-5 lift-off will be approxi-

* mately 37 days. It can be seen from Figure 3 that, for the above AAP-5



lift-off time, mission lengths of 24 to 39 days will result in splashdown

before sunrise. If a daylight recovery is desired for the 1-month mission,

deorbit must be performed on or before the 23rd day.

3. 2 CSM-ACTIVE RENDEZVOUS

This section of the document presents the reasons for choosing

the rendezvous plan presented in Section 2.

The fi rst question which might arise is why the terminal phase por-

tion of the rendezvous was placed in the fourth revolution rather than

earlier or later into the mission. The answer is that an earlier rendez-

vous would not have allowed sufficient time between the various maneuvers

for adequate tracking and CMC update. A later rendezvous would have

extended the maneuvers so that the final burns and the docking would not

have had sufficient ground coverage. The exact time of the TPI maneu-.

ver -within the fourth revolution was chosen so that the maneuver occurred .

approximately 11 minutes after the vehicle entered darkness. This allows

for acceptable lighting conditions during the braking maneuver which

occurs 36 minutes later. The sequence of maneuvers chosen for this

rendezvous constitute a nominal docking initiation (DKI) plan (NH, NCI,

NPC, NSR, TPI, and TPF maneuvers) with the plane change (NPC)and the

NSR maneuvers replaced by an NCC-NSR two-impulse combination. The ..

reason for replacing the plane change maneuver is that it cannot be

assigned any specific time in the plan; it must be performed at the inter-

section of the two orbit planes. This could very easily result in the plane

change maneuver occurring too close in time to one of the other planned

maneuvers. The NCC maneuver, on the other hand, is planned to occur

at a fixed length of time before the NSR maneuver. A second reason for

choosing the NCC maneuver is that, in addition to correcting the out-of-

plane error, it will correct for any phasing and height differential disper-

sions which might be present at this time. As a result, the NCC maneuver

will assure the correct height differential and phase angle between the two

vehicles at the time of the NSR maneuver. The NCC maneuver will be

nominally small because the launch vehicle will yaw steer into the plane of

the target vehicle. Therefore, this maneuver will probably be performed

with SM-RCS thrusters rather than the SPS engine. This alleviates the

problem of having to align the CSM IMU out-of-plane for the burn.

8



3. 3 CSM/OWS CLUSTER COMBINATION COAST

As was mentioned in Section 2, due to a lack of definition no attempt

has been made to simulate the portion of the mission between the CSM-

active docking with the OWS cluster and the CSM separation for deorbit

and splashdown.

3. 4 CSM DEORBIT AND ENTRY

No attempt has been made to simulate an actual entry. Because of

the preliminary nature of this document, it was felt that this was not

required. A study has been made, however, to determine the various

opportunities for a deorbit and splashdown in the prime recovery zone.

These data are presented in Figure 3.



le

^8/a



4. POTENTIAL PROBLEM AREAS

4. 1 LAUNCHVEHICLE PERFORMANCE

Due to the lack of spacecraft weight data for the AAP-5 mission, the

AAP-3 spacecraft weight data were assumed for this document. The fuel

and consumables loading were changed to reflect the usage for this

mission. By referring to Table 1, it can be seen that the payload margin

for a 25-day mission reveals a deficit of 2, 736 pounds for the two-stage to

orbit insertion and a deficit of 168pounds for the two-and-a-half stage^to

orbit insertion. The payload margin for a 56-day mission, on the other

hand, has deficits of 5, 512 pounds and 3, 414 pounds for the two-stage and

two-and-a-half stage to orbit, respectively. These figures do not include

reserves for the consumables; this addition should increase the above num-

bers considerably.

It should be noted that the payload capability design weight for the

two - and - a-half stage to orbit insertion is dependent on the length of mis-

sion flown. The limiting criterion is a launch vehicle structural limita-

tion; the total payload weight at lift-off cannot exceed 48, 000 pounds. This

constraint limits the amount of SPS fuel which can be carried and,

therefore, the amount of payload insertion capability gained by burning the

SPS engine for orbital insertion. A shorter mission requires less expend-

ables, resulting in a lighter spacecraft. This weight reduction enables

more SPS fuel to be carried without exceeding the stacked weight limit.

For this reason, the two-and-a-half stage to orbit mode will insert a

larger payload into orbit for the 25-day mission than for the 56-day mis-

sion.

4. 2 HEIGHT (NH)MANEUVER SCHEDULE CONFLICT

It is questionable at this time whether major maneuvers may bescheduled during the change-over from a two-gas to a one-gas system in

the CM cabin. In this case, no maneuver could be performed within 1-1/2

*This mode of insertion incorporates a CSM separation from the spent

booster and an SPS burn in order to achieve the final velocity needed fororbital insertion.

11



to 2 hours after insertion. If this becomes a definite mission requirement,

the height maneuver will have to be rescheduled or deleted from the ren-

dezvous plan. Rescheduling the height and all subsequent maneuvers later

in the mission would cause the final portion of the rendezvous and docking

to occur over very poor tracking. Therefore, it is felt that, if major

maneuvers cannot be scheduled during the change-over, the height maneu- .

ver should be deleted from the rendezvous plan. The NCC maneuver,

then, would become a major maneuver and would be performed by the SPS

engine. In this case, it would be desirable to schedule the NCC maneuver

approximately 180 degrees before NSR to minimize the radial component .

of the velocity increment required for the coelliptic maneuver. This plan

would necessitate performing the NCC maneuver over the United States,

resulting in less tracking data for the NCC-NSR solution. For this reason

it is suggested that, if possible, the rendezvous plan be left as presented

in Section 2.

12



Table 1. AAP-5 Performance and Payload Summary

Insertion Altitude in m i) 81 x 120 ;.

Launch Vehicle Payload Capability

Payload Target W e ig h t Design Limit

Payload B r e a k d o w n

C o m m a n d M o d u l e 2

Empty W e i g h t (Block II)3

A A P Modifications4

Expendables for Block II

Non-expendables fo r Bl o c k I T

C M - R C S

Service Module

Empty W e i g h t ( B l o c k 11)

A A P Modifications

E x p e n d a b l e s f or Block I I

N o n - expendables fo r Block I I

SM-RCS Propellants

SPS Propellants

Consumables Required in Additionto Block II

5

Food

L i o H ;O (metabolic)

E C S (O2, N 2)

Pressurization

Leakage

EPS (02. H2)

B l o c k U S L A

Total Payload W e ig h t

Payload Margin

'Based on a stacked weight limit of 48,

2 5- day2 stageto Orbit

( lb)

40, 000

38, 000

i

.

12, 121

1 . 3 2 9

(76

1. 193

270

Total 14,989

,

8 , 7 1 6

3 , 5 2 1

733

'14

2,157

5. 0,18 - -

. .Total 20. 159

!

S6

106

143

!

385

378

._ 5 7 2

Total 1, 640

3, 948J

40, 736

-2, 736

000 pounds.

Mission2-1/2 Stageto Orbit

fib)

38 , 5501

36, 620

1 2 , 1 2 1

1 , 3 2 9

76

1, 193

270

14. 989

8 , 7 1 6

3, 521

733

14

2, 157

5 . 0 1 8 -

20 . 159 : • • : • - • -

56

106143

385

378

572

1,640__

36, 788

-168

5 6 - d a y2 stageto Orbit

( lb)

40, 000

38, 000

12, 121

1 , 3 2 9

76

1. 193

270

14. 989

8 , 7 1 6

3, 521

733

14

2,454

5 , 0 1 8 '

2 0 . 4 5 6

173

325

323

385

1. 159

1.754

4, 119

3,948

43, 512

-5,512

M is s ion2-1/2 Stageto Orbit

r i b)

38, 0501

36, 150

12, 121

1 , 3 2 9

76

1, 193

270

14,989

8 , 7 1 6

3 , 5 2 1

733

14

2,454

' 5.0181

. 20.456 .

173

325

323

385

1, 159

1.754

4, 119

„

3 9 , 5 6 4

-3,414

The Block II CSMcontains consumables for a 10-day mission; aee Reference S.3Includes molecular sieve (159 pounds)

Includes solid retro package (1271 pounds). .

Consumables do not include reserve*;,

,see Referenci i.

13

^

01

0)

•1-1

• H

t(X)

U

J

nt

m

O

15

w

2U H

^•

fv j

< U

^a

H

1K §

oU

b ,££ •8

M

Ix v

S g•JH

d "O

5 Is0J 0

H•O

93«* ^ su *w

TI81a jd03

Is."8

I5fi

en .•»

;2-3

?21 — ^

'

•

l-g"?

Od~

oa

s S« ±jo «

fM

g

I

S

1 -*

5

NO

o00

Nr*.

s00*

S

Mnsa

V

n4)

a

4>

a

JM

§

NO

NO

O00

_

NO

ao

ro

t00

^2

Mnsa

aV

*

at

*

NONO

N

00r^

r-ina?N

NO

sWO

GaBm

V

oV

V

o

;H

or-

00r-

oin

<oNO

O

Ga

Bm

V

to

>

CO

CO

inNO

^fNO

NO

CO(M

into

rvl

<Q

«

B

m

4) 4> 4>

a a a4 ) U V

a a a

o v a>

a a

>* >* 2

a n a aV V V

a n

>< f c > «

o r- r- \o NO 10«f' J J iX in -r'NO NONO*« "* -*

N NO o vo tn in

3 2 3 3 2 inco o - r- r- IT*

• S ;

a ,2 an « ,2 ; os aa4 ) O 4 ) V V V 4 I . V O U V

•O 13hfcO 0

a u u a a a a a af t ) 0 ) 4 ) 4)4) 4 ) 0 4 > O 4 ) 4 >>*! tftf >*>" tH Z >• 2 tH JH

. * ;

4 ) 4)4) 4 ) 0 4 ) V O 4 ) O V

a a -a a a a a

t* > * S S >* 2 >^ EM ' 2 >* '^ >"

j

t n « aan a a;

« a

Q Q ) aa a) as ' (D oQ ) q) V ft) O 4)4) 4)4)

1

' i

S ° ' 5 ? M o 5 i n ™ Si n

S S S 5 o

*V o OI ^ M « * S OO « 0 » O >O O« i l ^ »

1 1 1 1 1 1 j

— comin —Nftot- —pj ul ro o 0

S S 3 2 S S o S ! v l ? j o o 5 2 2 S oc ^ ^ o . o o » a > m i n - . - , i n m o - m « < of * o u > o ^ ^ i l ^ ' O i n N i > i ^ i i n r ^ r o i ^ ^

i i i i ij

i j O u j C O O J ^ P Q ^ ^ i - ^ u j ' H ^ M Z

i

1 -III 2 1'S -! *• s ' " c * a s s s ^ ^ g ^ B g

5 3 - fi H 5' o o o a S';£! 8 S S H->

4)tfc1"

a4)

a4)

>*

4)K«. *

a

>,

> <

a

o

§*

oo

1m

Q

S

&

£ &* ft

0) 01

» V

Oa u4) qj

* B

£ £P* ?*

a 0)

>< ><

a toV 4)

>< >•

a to

o o

0 O

oo * inCO f-«

1 1

o o0 O

00o o

ro m

K(Q

§ H

M

c

y

D

obtSp

1*fl -

^aVftp

0

4 )

'S

f!N O a §

'Sttm

3 * 5~ 5 !• -S a

SReen

2Cb

se1

Mn

sg

n

14

< Ul™ ^^3

n )

"M

>*4

0)a{^ J

S

2^^

^^

•CO

ftn )

E H

CD

oo d.9.2J2 *^

• ** *rt

J O

U

o -§** 5 *~"

' S ' S >w

* o o *"*

• 2 EJ

~ « & X 0d W"3 — *

•2 S •" S« S • ? " 30 O ™—o « JJ 0

« .. •"!a * y ^

f-2"-

p ^ "3 c

ff-SjsOU-f CU<^ w

M4)

I n

jGH

S § * "3 «S m

B H —

• 3o_ H

1N

' *fc ^

?

^

' 5 £S 5d

2 x<

S " «5fl ft>(O n a

•S '5 u 9r t W .Hv ** u qp 3 M

S"5

£

a° t.

^JfZ

W

> < > <4* ^Q Q

>o min in

c! in-

1 1

vO O(0 CM

C O COC M C M

^CO

oC M

O <M

0 IM*00

00O "

O Oo o

A

5L

-o

A

5In

o

< <

*Q

1*1

•aC O

oo

•C OIM

_

00

?IM

< n

w

r-

IM

in

M

«

o

0

d

in

IM

IM

GO

00

«4

0

N

h-V

V

2

V

X

>*^jQ

«r*

C M "CO

tn

f»N

1

m*t

5

C O

to

CO

r-

^

m

o

o

o

d

•*

^2

CO

f\rM

(M0

CM

m

U

00

.90)

C U

8g

35o

> ow^

ai

1

CT-

CO

O1

in

5

wurf

N

(O

**

^

0

1

CM

fO

in«H

1

^

O

C M

fOO

n

1

o

e

v

Cm

n

(N

M

n

U

â

CO*0

c*in

l-00

r-M

1

o(AIM

3N

OT

C O

t-

r*

m

2

«•

r*IM

->

^

sD

«4

fO

o

CO

CM

inmrO0

^

n

opcN

RM

U

8g

3

3Q

r-CT*

d

1

ON

in*4

1

inCO

CO

M

C O

tf

m

vOin

0

^

m

i

CM .

I

in

r-

PO;

?

Ô

ino

*

d0

ennP

In

(T

M

n

H

^,

<Q

„ -.

C T1

(1"

OÔ

'•

1

,

o

C M

infsl

•

tn

B !

in

CM (

. i

C M.

CM*CM • .-

~[

in

r-

i

fO

sO

CO

« 1

C O '

mo

ji

*:

*+•

N

1

emnPeFn

(T

M

n

H

ao

id

'•S

'.gd

9^r i

"3

1

0)

•3•oV

uto

u"O

Jn

30)

_

d £•S P

"r t *

° ° r t

a & '^

r 2 S0 MO

E * «

.H 'O n

.S B °o= 8 ? - C

• 9 - 8 -

:|:|a.m a) EO O O0,0.0

i i i

X N > «

*; .

15

00 Is- I

s- Tf

o o o o

00 —.rt

— bO «.

 Ot OH JJ

bo

2-

*u

&0

. aT)

^ s

s ^ s• ^ " > - aS ° 7tL) "

M (U -H

C U M (Hr ^

oo

~ B•in ,xto to

• a c u " 51 S - ' ^-< d '.o -S j*ft T) o

£ n d

o § 1U S^

N

x

c uCfl

ton)

c o

c o>N

CO



pN

PX

u n

c u•4-1

C O

i—I

U

co

O

W

uc uto

'igM

J

W

(Vj CO 1 lH

m oo ro ooO^ C*^ "^O ^3t"- CO OO CMO^ C** ^ J

C O C OM

O O O O

mo

W

ooCM

NO

O

C MC M

mo

H

NO

fM

OI

II

X

ii M n

N QX

QN

m -^ CM oo coo o o o o

W

oo

in(VJ

C O C O

o

W W W

oo oCM

CM CM CM

O CO

CO COCO

O COco 1

s-

CM CM Tf CONO (M - r t ON

o o o

. II II

rt o

00o

H

H

f

^•

CO

CMCM

O

II

<

CMO

W

oNO

^

CO

or^ -CM

on

W

CMO.

W .

omiH

O

O0

s

ooC M

o

'II

M

CMO

W

CMmCMin•r

CMf

•*.

O

II

0

COO

H

mCMoo^•4

CO

00T H

*H

0

II

ffi

COO

W

~r-l

' *f

O

NO

mCO

CO

on

J

o

C O

in

oC M

oo

ch

too

AbO•H

c!

•H

B

1 ^

toc u

ubO

Oto

-B

re

H

O

Xn >

iX

16

rrt*

d>

3

.3

oU.

CO

0)

< a

St

LT»1

P-i<4^rH '

flj

. aso.£ .0)

W)a• 1 - 1i?o

1 — 1I— 1

oW

C O

cc

rHM

"c d4-*•H

rQ

O

.

Q)rrHr"

c dH

r-o

W

POCM•rH

00

*0

00

mo'

n

X

h OO

t J w(U

> §a oO Ô

*OJ °°lj Is"

fll^C O f^J

^ o

s „u >

ooo

W00

•vO

vO

PO

*H

CM

O

II

<

-.

U

VCO

a ••H

s"'

rfS

c d

2

oo oo0 O

W H

in mCO \OT H oot- POt-t -rH

O -»H

r- o•vH TH

O0

1

,1 1 II

>H S

so oooo

W H

- 3xD vO

• < # m•rt ON

00 "tf

r- \o•*H (7

s

o o

II II

u a,

oj oooo|

H Hoo in

• "^ t*"oo invO f^

c ^- r--• 0000 00vO 00

o o

II II

W rH

o

POm

mo

^H

00

0o

E H

U

in <*o o

W W.

P O r-o mt^ ô r-m -ôo oP O o o

oo ooo

i

n n

Q QrS r*

oo ooO O

W H

Q - H

O t

CM 00O }<Tt m•rH m

OO vO

O oi

n ii

Pi OJ

PO PO

00

w wo in— " o o^HH ^H

^H -

(7s OO"« ooOT<

T •»!

00

II II

0ffi

^

w•< foo0s

* *xO

m00

oi

ii

QN-

o H

W -

t^ 4>in >0 J

o uC JN IHTH *d

00 SCM **

0"$at

• H

II «J

•<

J

^1

W^JH

0

rO0000oo^00

oII

^

r- ooO 0

H W

oo mPO •'-'-vH

m oô oo•vO ^5

•^ oo

;m --Hooi i

n n

b^ ^H

m oooo

iH W

m oPO ••-'PO 00

OO •<;}<

PO O

m vOCM sO

00

II II

> U

00 "H

o o1

H W00 00t^- t^-• < 4 < mP O o ooo0s

0s

••H 00

00 00

o oII II

< w

oo mO 0

H W

m vO00 -tfm •«-<sO O^ rO "H

o -<tTH 00

o o

II II

N QX

oo ooo o

W H

CT V0

xQ ^•^ r^-

ro ^00 OPO ^^[ •'o oo

00

II II

P k P ^ J

00 PO00

w wTH vQ

• ^ H m^ r^ ^^t*"™ O^

r- oo00 ro00 O00 -H

O O

II II

~ o

00

in^H• •

• ^

PO

0000

0o

H .

a

< * - *o o

H W

C~ i * 1

r^ ^0PO •«-<

^ T<

•^H -<-H.

. "

O^ 0s

oo oo00i i

M II

Q P>-". N

.

CM 00 7to o O

£W W ~

o o r- «

xo oo $

f . f*. Q)CO CT 'H

P O c> rt**Q t*- ]5oo oo

o o di -3

CO

n n cd

O < &JJ

PO O00

H W•*H ff)

00 tin inm inIs- -^r^ PO•< # o o•rt 00

00

II II

f f i A

t- 00

0 O

W H

oo POCM 00•rH ff)

o r-oo moo o^m oo

m -"Hoo

ii n

X !*

m PO0 O

i

W W

oo oom c~-

v£> 00• PO0

sÔ

•^ oo o o o

o o

II II

> o

oo —ioo

i

W Ho ^* r^• r-Is* ^^

oo coPO Ô•rH CO

00 O00 -H

oo

ii n

< W

ooo

H

ooosO

00^t*o

•ô

1

II

N

ooo

W

3vO

oo•*H

• JH

CMoo

o

n

PH

00o

Ho0s

vO

00[

ooCOCM

oII

I-H

00

00CM

cr-

• •

POOJ

0o

H

u

in ^rfo o o

W W W

P O oo ooTH oo ooo •* mP O xO oooo — rôo t*- oPO ^ C

oo oo oo0O0i

M II II

Q P PX >< N

oo oo ooOOO

W W W

[•»» \jO i

o -rf ooo o P O o o

P O oo oof^ . -r^ ^P O r^ oo o oo f-00 00 00

ooo

ii ii n

DH O <

J

PO PO PO

o o o

W W WO vOTH

r- so or oo mP O o o o oCO t (7s

Tt< C^- OÔ -rt< [•rH TH .rH

OOO

II II II

U ffiJ

L

r

cL

L

L

C

r

< .

H

^

r

*4

y

t• 5 1 -

17

T3<D

•IO

(J

C O

s2

3

ac d

i-O

PH

^

i-H

ri

.36o

<D

£00

.3[>

o

ofc

C O

JH

c o

(1)1— 1

Wt — nj

• H

O

•

"*

(Uf— 1rO.

c dH

00o

W

r-T HorO

NO

OCM

O

U "

5.

O J>

 S >'•M

U

InrH

° ooU o

W

ro

O\rO

TH

0000

oII

<

_,o(UC O

.3sfH

s >c d

TD

r- r~o o

W W

r- r-ro ON00 NOCO Oîn THN O m

m NOl> 00

o oi i

n n

ix N

O roO O

W W

m mr- ON

vQ 0s

00 ro•xt* THON 00

NO TH

O O

II II

tj p_<

TH (\J

o o

H W

rO NOCTN ror— roNO rO•x t< OCN 0

s

TH 00

TH (\J

O O

II II

HHH

o

C Do

oo'00

C DCD

TH

o

H

U

•xf moo

W H

NO l>

m THoo oooo m•xt< OO

O OJ

N O oo

oo

n n

Q Q

00 CMO O

H H

^ ON

CO CM

CM THl> OTH NO

'TH TH

00 00oo oo

001

II II

PH" O

rO COO O

HH

CO sO^ sO

CO COo*^ ^în ooON t~~

O •r}<TH TH

o on n

O ffi

mo

Wt^T4

O

M

inoo

TH

o1

II

QN

^ _ ^

PHCO

O £

w S jTH £

t- a>00 jjj

NO ôo A

^ -H

0 0-I *iH

< °i-l

ON!

o

H

romoNO -

00

ro00

O

II

^

t^ CO00

W H

rO 00•xt« inO^ ro00 NO00 NO

i 5 O^NO 00m TH

oo

n n

K/> SrS r

1

m THo o

W W

rt< r-

CO 'Is-

oo O'NNO rO

r^ * **"*o pm NO00 NO

o o

n n

> a

00 0000

1

w win O~NTH QO

NO rOTH 5

NO 00rO NO00 0000 TH

O O

II II

< W

00o

U

orO00

.00in

2THo

1

II

N

00o

W

ON

(7s

^4*

00ro

00CO

o

II

PH

ooo

-,

HTH

oo00f-^

oo0000

o

II

l-H

in

tJTH

• •

TH

m

CDo

TH

o

H

U

m rfi00

W W

00 ro00 00T H roro 1

s-

r« - o o .ro m

ro m00 00

001

n n

Q P*v* Sj?S t"

oo ooo o

H W

oo NOro -TH 0

s

rO TH .t^- 00ro NOoo o"oo m

O <D

n n

PH Oij

oo co00

tt tt

T H m0" **

^— 1 f^-

m in^ * o ^^vD f^00 -Nt<

ro -

00

II II

0 E

T } *o

' w.in00

.00.ON

f^ .

o: ;.CO

0

II

p .N ^

PHHN«»

ro rj0

1H "g

•rH

rO H

NO . r^3oovO ôo 2•>• ™00 -3

< = » ' ^H

" .3< Sj

H

.roO

W

00ro •OOO0N

m .rfi

00

O

II

4

oo oooo

H W

rO -com ONl> O

rO fON f*

.00 rOON TH

TH TH

o o1

II II

X >-"

' •

in oo o

W W

ON oO00 roNO NO

m roO 00TH (\J

m o00 TH

o o

II II

> o

00 00o o

1

H H

ro --1

r- f-oo -r*-xO ON!

o m•xt

1CO

oo •*oo oo

00

M n

< H

N O in00

H W

ro mNO O

OO TH

m roin NOO 0000 ONO -H

'0 0i

n n

N PX

ro 00O O

H W

xO < " " > •

oo -o^f ON

NO O

00 NO00 <"">TH 00

TH 00

o o

II II

PH PH

00 roO O

H Wo o o oro ro00 0

s

IN- 0

C D r-ON in

oo ro00 "H

00

II II

HH 0

CO

odo• •

00in • ...

TH

o

TH

o

H

U

in moo

H H

06 ooON "xt*

OTH

f*» f

TH TH

TH TH

O'N 00TH TH

001

II II

p p>H N-

00 TH>:o o

w w•xf ro00 l>NO 00

xO NO

xO 0s

OOO

oinNO TH

oo1 1

II II'

0 <HH J

ro 00O O'

H H00 NOm oorO 1>m T}<r^ - r^N O ro^^ r^TH TJH

O O

II II

ffi 4

18

T)4)P

.11

•4U

cou

C O

Vicu

&p0)ccd

Sinift

<;< •*NrHn)

.3SosDrj

•5ofl

.3>!>O

rH

O

rH

CO-!->

c(U

0)rH

W

rH<*)4->• rt

rO

M

O

-44r

<D^H

rO

«t

H

hft

• tL

d•H•*•»

rtN]•Hf-H

n)

.Sfc

c uC O< tf,3ft

mna• n

0)

H

— u0)C O• •

.s• arH

'•?.

n!. T3

IN

o

W

POooON

•wH

oo0NO

00

o1

II

X

ino

W

fOO•»H

•*H

IN

omPO

o

n

>

00

owCOoNO

o.CO^ <

.POPO

oII

<

ooo

wc^POTH

t~ -NO

NO

o^•>H

o

- II

>H

•«H

o1

H

•vf

to00•*ON

ON

oo

o1

II

0

PJ

o1

H

ON

O

moPJNO

[N

Tl

O

II

.H

IN

O

W

m•*H

PJ

NO

NO

CO^fNO

o1

II

N

POo

Hm

mr^ON

NO

O

NO

NO

O

M

ft

PJ

O

W

or~m•*H

o - s0000PJ

o

II

r-i

oo•

CO

CO••

T fCO

f\J

0• •

•*H

O

H

^0

ino

W

r-poTH

o•*TH

PO

PJ

O1

II

QX

00o

W

in

mNO

POTH

•*PJPJ

o

II

CH

PJ

O

W

COtN -TH

PJTH

NO

NO

PJ

o

II

o

•*o

wNO

r~NO

NO

IN

•*mNO

oi

u

Qr*

POo

W

oTH

mNO

oON

COt^-

o

II

O}

ro

O

W

COr~c^

^*nNO

•< tTH

0

II

K

•*o

W

t^[N

t

CO

PO

miON

O

II

QN

PJ0

WNO

TH

NO

ON

00

NO

NO

TH

O

1

II

<

J

CO

O

W

P J00c-0or-o^PJ

oII

J

19

•» ->C ObO

T)

^P Q-» jcnji-H

CO

ftOt-(

k

C O

U(v;^H

••H

C O

r)-(

11c tt

C O

&CO

lA

s<!

•

IT>

0)i—

• sH

T<CO u

U w

^ S SM

"0. '. n. r-1 •*

H

SH w

fZ, CO

c o -r|JPcn J

S *-«« fi

o ' S S " ^ ^

iiw--|D H £C O Cij

CO

< £ ^> 1 PH

•^Si

rd ^•M CO

(U

Q -"HC O co 1

^^Slc o 2i|

C

m

ns

C

g

ao

w

g

=35b

1so

e

+Xb

n

c o CO §** r i .,4ti

Z > $0) PH n!> .-, -^ nH n ?

rt

" o p ,S ^ a>2 ° wro fli

•3$ S>H U CO

( U

r^ o --^ rj '

•* \O IT)• -^H

ro

1

(U

« be3 h.g ' .

g- ? ftd > 5^ -. 5 s c

 'S ^ C U « ' Sh

^^^

: ~ S Ms n - i ' S f s « « s-t « i g W r t S S « » w )u

« w S ^ °^Ut

«5w>n °

M'o'52

t Q>n °

h• "2

• a ' S Ss

* « -alS Sr t

« - a ^ - s «gSC h 

l^u £§^ 'I^0-*-!

6-- !•"»••"i U „, n) o C i - p g j c o . fj m

OfVJCO - H C Q O OfMfl ) . H C O - ^ OfM .H t*

S P Z Q S P

• aH

ti)

dd CO § .

•22 .2?

a s ^ . ^• £ . 2 > D j3

l

n J co 5 3a o D

. o- m

oo

<« 0•*H

/vl •r\j

fih

43

C O

O HC O

-PCO

: ^• » ~ »

•;5,4-1;rfl

be•H

C O

ffi

C OU

tiC OhC O

« * - ((U

0)

CO

20

CO

c o

"S

rt

ft

n)

O .. -H .

•rt (VICO O

1-

vO CO

O -rt•rH (M

vo . m vo m

< a

ioU

0)&0

TJ

C Q

C O

o•*H

O

(M

CO CO

rtH

0)•rt

C O

dc o• sV>

w

rtH

H_

goP

1C O

ft.G

P

^ • ' .C O

O '

E 3

t:rtJh

H

C O

• ftCO

ao•rt

1 3r—

CO

srtH4J

C OU

CO CO t o . c o

1 5

igm

.D .

R

•4->

• t o'-0

• > - »

: - 3

o

e

U

irt

2 -r!

in

o

Cm

OO^

e

3< u

M• rt

5 !pR

V00rt

1-1i-H

21



uC D ~~.ftrO NO

o . in

to

O

r--

mr-

«n J

OrH

vO in

(Mro (M

TJC D

i•rH

t!oU

C D

T)

P Q

to

|W

CO OPJ

1O

fln ) t o c o

ft

OH

ft

to

U.CO

ft

W

• art

to

to

co

rttO

a )H

SP

b

n

-R

tranao

S S

PH

rto

. ce:h

e

I N -

t- rO C M

r5

- 3.. o

e

c

e

:h

e

to •* "* X

&*'.C O '

.H vO

0 •

rH "*

So'S V HC! o

aon

saon

1 r*

a"2•u

S xo

0o

• H•*•>

ri• • t —

C D C OC O fjn ) r tU rH

' g N£

- Bft^5

b - irH r"

Q

rH

(U

S/n

C OH ->aCD

>W

w

tirt

su

• 1-(-M

• - ^ 1• » §»—U

1*-dsO

Q4J.

.3w

f t . •

ra

QrC

CO /H

5 " . § •W h

• ^ '

3. CD

. P

GO•H

: 3D

,, H

CD

CO

nJrC

fti-H

n>

e

n

•H

t-tftK

ao .T»"»».

n )•H •+>

1

&0R

iM

«

C D"C OrH

§u

T3•H

2

_ _ ^kftH*

-"

C D

T3d

.• s+ >

3

C D|O

C O

c d

(H

CD

•M

CO

r3

O

to

Sabe

C D

rf.3rH

ftO.

V C O . .

x £i°

-.85: B ' g '- » - > • *w

C coO bO

•H g

" S - j i00 rC

•r| &o?• -H

rt to2

to£o5rH

1O

"F1o UP

22

T3C D

3a

•H-MfH

§

(J

- i _ >0)

00T33.

O QH-1-1{H

« isOA

ftoIH

P vcourt

i•8a t;

C O '

P H :c o :in'

i

P..

<.<

•

in

c u

3

C O

o-.0!

iC O

4->

enii —

i—4c uaoM

f\Pi

T(0)C O ^_

S £ft —

O• iH

p

Ita 2HrU

S^oa

' ^" C M

C M

T^H

{MC M

c o H- ^ 51c o ^ i|

>c d

* ->f^4

< uQ

C O

u^.P E j C O

1

£s-co

C O loln. dJm t T t ic o i H

Cm

n

s

d

OWcuewg-

<

inl

9

CMCsaumo

m

_ _ iTJ(UF H

.v

2

dymsocod

•ri

-M

s.0

•»—

• ^ o* fT"

1

1

ti

0se

fo

e+X

anao

•*H

r-t

Ot-(

Lus1

p

cnm

m

n

cn

ft

r> -

T^H

amapeo

C O

O -H

•rt CM

vO

mC M

CM

CO

CM

o

a

pe

apeo

< u < u

a art rt

C O C O

m o-

00- c• f t

ed

ayb

oed

o

Z

CO

ovsO

CO . CM

.00

.•'00

ooo

C O+Jc0)

p -cfl

C O

Es

A

u

CnroO2U

C O

OVH

O D

m

n

C

M

Spao

N

vg

on

Sg

n

IM

UAgm

U

ag

.

D

b

M

n

S

ohDm

n

SM

S

n

an

Je

son

sO

-

23

"O0)

c

flo0• — *•4-J

Q )DJ O

1

ctc

r— Hr— 1

CO

OrH

0

to

CJ

1

*>

toT)

nJ

to

tomi

<]

in

C D

to

O

OHI

W4J

9i — rH

0)

ao

OH

TJ0)CO

OrS

•H

Q

oo

CNl

'rta _,"J /^"C ^Q

o "-*

ooNO

(N

to . — J (M

to C±J <•"

^r-H

Q

to0

O H "wi (i

to

to "ml

to £|

C O4->

!H0)

sa0

U

(M m

in

o4

r tV grH rrH

o'SCO

O JrH

IU

43 +

O »

§

(NJ

oo

oin

cSH->

OH

col --.sO COCM (M

fM

NO

(M(N

ooo

CM

m

(NlvOin

POt\JCO

CO

in

< u)H

a.C O

ni

V

stdW

in•*(Nl

m

oo

om

O

H

C OC O

'H

H

i—H

c t)3

•H

C O0)

OH

CO

H->

•rHfO

010fi

M)ti

'So

riO

nt

rH

5

bO(H

^3« so

.JrH

a«•Hf

%•H

C O

c o"AH

><

« tT)

m(N

^v

§•HJ

<D ."

OH f!

.2 ft) corA rO '"

a)' ^

ii ^u

rta)

flj <*H

C O

(U

•H

c d•u

0)C J

£&0C

r?

O

n)

vS

bOa•|H

c fl

r5

e•H

o•HCO .

COrH

C

nt

-Oin

24



co

00

O

U

U

w

oin

iOn

GO

25



1

1

i \L nI THl

i

-o

s

1rr

I

8

oQz

8 S

oCN

8

o

o

o

O

(Sdd) HinWIZV HDNnVI13TIVHVd dOd AV 3ONVH3 3NV1d

co

• rH

(0c o

ddo-idn SMO woyd AVQ HIN

S3NVd HDNHV1 S-dW

(HO

O

C

£yc

IH

n)C

(DIH

3 )

26

<

oo

o

ou_

LU

5

coN

Ou< u

a J

C O

0)

C O

C D

Oaa,

O

OU0)

c uM

3CuO

(ilH) 3NOZ D I 1 N V 1 1 V 1S3M N l 3W I 1

2 7

1VDO1

u

O

1

aFI—

g

«i

1L i

s ?

3

a

.0

'8

-a

- s ?

_ o

Co

LC

_ o

_ o

I

i

8

°

N.«T3CV.

V

Z 25 W§ U

o - 2 2 3S t S <u*~ j "J r<

« ^ '8

1 S

«

s 3•< U)

o

o

AAC

28



M

gN0)

T3co >

P C ;

2CO

u

ont

T3C

g

oA

W

in

(oaa) aaniuvn29



.o

C O

O

C O

(IW N)Z 'iN3W3DV1dSia

tf l3

O>N'0)

T3d0)

0)

e n U

0 0)

d0)

re

W )d

^ cu o" -r-4

OJ 4- 1

(U '

d H

f^ ^_^, "

5 2u

.S " r t(U -^

E a)

--^ w

(J

C O

^O

toU

vD

bo

30

00

CO

2oNID

T3aVffj

CJ

nt

1)+->

C O

3i— U

W

O

5wU

sO

BCD

O (IWN)Z lVDIlil3A

CO

31

J, Lj -! ili- lit -4--i- « il- -1"-it — ly W -M S"51 iiil iiif ii.i III! lit hi! lit Kl . il l ,11 Ml lilt nil IB ffl

(iw N ) 3ONV)i jAiivnaa

w

oSI

0)

a30)art

Na >

T3ti0)

C ti

o;>

U

(U

0)00a

s

tuO 0)•rH >>

ffi **

2•

r^

i-t

1 I I §

(Sdd) 31VX 3ONV)I 3AiV13i

32

e n3O

N0)

TJC0)

B Jo+J

co

inPe

-A

v

Rn

C O

U

V•Unl

C{

a)

B J

TJcnt

mW >Cnt

BJ.

v

2" tf

t-

< uM

% 8

(IW N> 3ONV8 3AUV73JT

1 ' 1 1

(SdJ) 31VD 3ONVJI 3AI1V13II

33



OW S CLUSTERORBIT

CD I AAP-5JNSERTION INTO 120/81 ORBIT

(D HEIGHT (NH) MANEUVERRESULTANT ORBIT 241/81

(3) PHASING (NCI) MANEUVER iRESULTANT ORBIT 241/157 ;

@ CORRECTIVE COMBINATION(NCC) MANEUVER • '

(5 ) 'COELLIPTIC (NSR) MANEUVERRESULTANT ORBIT 243/230

® TERMINAL PHASE INITIATION (TPI) MANEUVER

(7) TERMINAL PHASE FINALIZATION (TPF) MANEUVER

Figure 8. Orbital Geometry/CSM-Active Rendezvous

34



REFERENCES

1. "AAP-5 Consumables Budget, " NASA TM 67-FM7-191, 3 August 1967.

2. "AS-503 Network Support, " NASA TM 67-FM13-67, 20 February 1967.

3. "Preliminary Estimate of the AAP-5 Propellant for the PreliminaryReference Mission Profile," NASA TM 67-FM7-172, 24 July 1967.

4. "Preliminary Mission Profile for Apollo Applications Mission AAP-1/AAP-2, Revision 1, " MSC Internal Note No. 67-FM-112, 1 i August1967.

5. "Revised Payload Weights for AAP- 1/AAP-2 and AAP-3/AAP-4, "

Reply to NASA TM KM-60149, 18July 1967.

6. "Station Characteristics for Apollo Support, " Prepared by FlightSoftware Branch of Flight Support Division, May 1967.

AAP-5 Mission Profile 671010

Documents

Transcript of AAP-5 Mission Profile 671010