8/6/2002 AIAA/AAS Astrodynamics Specilaist Conference Martin.Lo@jpl.nasa.gov...

8/6/2002

AIAA/AAS Astrodynamics Specilaist ConferenceMartin.Lo@jpl.nasa.gov

Min-Kun.Chung@jpl.nasa.gov JPL Caltech

Lunar Orbit

Lunar Sample Return via the Interplanetary

Supherhighway

LanderSeparation

Lander

Orbiter

LanderReturn

LL2 Stable Manifold Insertion

LanderReturn

Lunar Sample Return Mission

MWL - 2

Martin Lo, Min-Kun ChungJPL

Agenda

• Lunar Sample Return Mission Overview

• Baseline Mission Scenario– Lunar L2 Case (LL2)

• Mission Performance Comparison

MWL - 3

Mission Overview

• Goal: Collect and Return Lunar Samples to Earth– Aitken Basin on Backside of Moon, (180°, -57°)

• Launch Combo, the Combined Flight System

• Communications Orbiter – Desire Continuous Communications Coverage

Between Earth and Lander Module

• Lander/Return Module– Sample Collection in Sun, ~2 Weeks Available– Return to Earth (non-specific target)

MWL - 4

Key Results

• Metric: Total V of– Combo– Lander/Return Module– Communications Orbiter

• Trade Time for Total V

• Best Case 1446 m/s Less than Conic Case

• Baseline 1020 m/s Less than Conic Case

(days)Total

V (m/s)-Conic V (m/s)

LL2 146 8586 1020

LL1 151 8663 943

EL1 553 8160 1446

Conic 23 9606 0

MWL - 5

MWL - 6

Key Concepts Used in the Paper

• Lunar L2 Halo Link Earth to Lunar Backside– Colombo (L1)– Farquhar: Halo Orbits

• Dynamical Systems Theory– Poincaré, Connelly, McGehee– Gomez, Jorba, Llibre, Martinez, Masdemont, Simó

• Hiten-Like Transfers– Belbruno, Miller– Lo, Ross– Koon, Lo, Marsden, Ross

• Heteroclinic Connection Theory– Barden, Howell– Koon, Lo, Marsden, Ross

MWL - 7

JPL LTool Team

Martin Lo Section 312 Task Manager

Larry Romans Section 335 Cognizant S/W Engineer (Marthematica Developer)

George Hockney Section 367 S/W Architecture & Sys Engineer

Brian Barden Section 312 Trajectory Design & Algorithms

Min-Kun Chung Section 312 Astrodynamics Tools

James Evans Section 368 Infrastructure S/W, Visualization Tools

MWL - 8

Case LL2 : 1020 m/s Cheaper Than Conic

• LL1

• LL2

MoonEarth

• EL2

• EL1Case

T (day)

Total V (m/s)

LL2 146 8586

LL1 151 8663

EL1 553 8160

Conic 23 9606

BASELINE CASE

MWL - 9

Case LL1 : 943 m/s Cheaper Than Conic

(day)Total V

LL2 146 8586

LL1 151 8663

EL1 553 8160

Conic 23 9606•

LL1•

MoonEarth

• EL2

• EL1

MWL - 10

Case EL1 : 1446 m/s Cheaper Than Conic

(day)Total V

LL2 146 8586

LL1 151 8663

EL1 553 8160

Conic 23 9606•

LL1•

MoonEarth

• EL2

• EL1

MWL - 11

LL2 Case: Direct Transfer to LL2 Lissajous Orbit

• Lunar Transfer

• LL2 Lissajous Orbit

• Lunar Landing

• Lander Return

LanderReturn

MWL - 12

LL2 Case: Trans-Lunar Phase

Trans-Lunar Injection3122 m/s at 6/14/09

Earth6/14/90

LanderReturn

LL2 Insertion570 m/s at 6/18/09

Lander Return

Earth11/7/90

MWL - 13

LL2 Stable Manifold Insertion

LL1LL2

Trans-Lunar Orbit

Lander Return

Lander Orbit

Orbiter

Lander LL2 Departure: 35 m/s at 7/7/09

Lander Touchdown:2335 m/s at 7/17/09

Lander Return:2424 m/sat 7/28/09

LL2 Case: Lunar Phase

MWL - 14

LL2 Case: Earth Moon Rotating Frame

LanderReturn

MWL - 15

LanderReturn

Orbiter

LL2 Case: EME2000 Inertial Frame

MWL - 16

LanderReturn

Orbiter

LL2 Case: Sun-Earth Rotating Frame

MWL - 17

LL2 Case: Mission Sequence & V’s

Mission SequenceDate

(2009)T

(days)

Combo V

Lander V (m/s)

Orbiter V (m/s)

Translunar Injection 6/14 0 3122

Manifold Insertion 6/18 4 570

LL2 Halo Arrival 6/25 11

Lander LL2 Departure 7/7 23 35

Lander Landing 7/17 33 2335

Lander Liftoff 7/28 44 2424

Earth Return 11/7 146

Navigation 25 50 25

V Total 3717 4844 25

MWL - 18

MoonLL1LL2

Heteroclinic Connection

LL1 Case: LL2 via LL1

• Insert into LL1 Stable Manifold

• Heteroclinic Connection for Comm. Orbiter

• Lunar Landing from LL1

Lander Departs for Moon: 95 m/s

Landing: 2330 m/s8.5 days later

MWL - 19

LL1 Case: Mission Sequence & V’s

(2009)T

(days)Combo V (m/s)

Lander V (m/s)

Orbiter V (m/s)

LL1 Halo Insertion 6/14 5 600

Orbiter LL1 Departure 6/19 10 14

Orbiter LL2 Arrival 7/7 28 0

Navigation 25 50 25

V Total 3725 4899 39

LL2 Case

MWL - 20

EL1 Case: LL2 via Earth L1

EL1 LOI 60 m/s

LL1 LOI 13.2 m/s

• Reduce LL2 LOI V: Launch to EL1 Fall to LL2

• Once There, Follows LL2 Case

Earth Launch 3193 m/s

FAIR/DART Trajctory

MWL - 21

EL1 Case: Mission Sequence & V’s

(2009)T

(days)Combo V (m/s)

Lander V (m/s)

Orbiter V (m/s)

Earth Launch 5/30/08 0 3193

EL1 Insertion 8/29/08 91 60

LL2 Halo Arrival 6/25 391 13

Navigation 25 50 25

V Total 3291 4844 25

Reduction by Order of Magnotide

LL2 Case

MWL - 22

• Conic Trans-Lunar Orbit

• Lander in 100-km Lunar Parking Orbit

• Orbiter in Highly Elliptical Orbit– 100x8700 km, 12 hr Period

Conic Case (S. Williams, JPL)

MWL - 23

(2009)T

(days)Combo V (m/s)

Lander V (m/s)

Orbiter V (m/s)

Separation 7/17 1

Lunar Orbit Insertion 7/20 4.5 979 481

Lander Apoapsis Burn 7/20 4.54 23

Lander Landing 7/20 4.58 1703

Lander Liftoff 8/3 18.5 3220

Earth Return 8/8 23

Navigation 25 50 25

V Total 3125 5975 506

Conic Case (S. Williams, JPL)

MWL - 24

Libration Point Mission Lowers V

• Saves Up to 1446 m/s!

• Provides Continuous Communication

• Trade V for Time

(days)ComboV (m/s)

Lander V (m/s)

Orbiter V (m/s)

Total V (m/s)

-Conic V (m/s)

LL2 146 3717 4844 25 8586 1020

LL1 151 3725 4899 39 8663 943

EL1 553 3291 4844 25 8160 1446

Conic 23 3125 5975 506 9606 0

MWL - 25

• END

MWL - 26

Lissajous Orbit

LL1 Stable Manifold

MWL - 27

MoonLL1 LL2

Heteroclinic Connection

MWL - 28

Lander Departs for Moon: 95 m/s

Landing: 2330 m/s8.5 days later

MWL - 29

Martin Lo, Min-Kun ChungJPL Interplanetary Superhighway

in the Earth’s Neighborhood

• Collection of Invariant Manifolds of Quasiperiodic Orbits in the Solar System

– Coupled Three Body Systems

EARTH L2 HALO ORBIT

LUNAR L1 HALO ORBIT

LUNAR L2 HALO ORBIT

LUNAR L1 GATEWAY

MWL - 30

Mission Design with LTool

• Lissajous Orbits and Manifold

• Trans-Lunar Trajectory

• Lander Sample Collection in Sun

• Lander Insertion Trajectory

• Heteroclinic Connection from LL1 to LL2

• Interplanetary Connection from EL1 to LL2

• Lander Return Trajectory

MWL - 31

References

• Barden, Howell, Formation Flying in the Vicinity of Libration Point Orbits, AAS 98-169, Monterey, CA, 2/98

• Barden, Howell, Dynamical Issues Associated with Relative Configurations of Multiple Spacecraft Near the Sun-Earth/Moon L1 Point, AAS 99-450, Girdwood, Alaska, 8/99

• Gomez, Masdemon, Simo, Lissajous Orbits Around Halo Orbits, AAS 97-106, Huntsville, Alabama, 2/97

• Howell, Barden, Lo, Applications of Dynamical Systems Theory to Trajectory Design for a Libration Point Mission, JAS 45(2), April 1997, 161-178

• Howell, Marchand, Lo, The Temporary Capture of Short-Period Jupiter Family Comets from the Perspective of Dynamical Systems, AAS 00-155, Clearwater, FL, 1/2000

• Koon, Lo, Marsden, Ross, Heteroclinic Connections between Lyapunov Orbits and Resonance Transitions in Celestial Mechanics, to appear in Chaos

MWL - 32

References

• Koon, Lo, Marsden, Ross, The Genesis Trajectory and Heteroclinic Connections, AAS99-451, Girdwood, Alaska, August, 1999

• Koon, Lo, Marsden, Ross, Shoot the Moon, AAS00-166, Clearwater, Florida, January, 2000

• Lo, The InterPlanetary Superhighway and the Origins Program, IEEE Aerospace2002 Conference, Big Sky, MT, February, 2002

• Lo et al., Genesis Mission Design, AIAA 98-4468, Boston, MA, August, 1998

• Serban, Koon, Lo, Marsden, Petzold, Ross, Wilson, Halo Orbit Correction Maneuvers Using Optimal Control, submitted to Automatica, April, 2000

• Scheeres, Vinh, Dynamis and Control of Relative Motion in an Unstable Orbit, AIAA Paper 2000-4135, August, 2000

8/6/2002 AIAA/AAS Astrodynamics Specilaist Conference Martin.Lo@jpl.nasa.gov...

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