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

EL1

Moon

Earth

Moon

LL2

LanderSeparation

Lander

Orbiter

EL2

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

Lunar Sample Return Mission

MWL - 3

Martin Lo, Min-Kun ChungJPL

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)

Lunar Sample Return Mission

MWL - 4

Martin Lo, Min-Kun ChungJPL

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

CaseT

(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

Lunar Sample Return Mission

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Martin Lo, Min-Kun ChungJPL

Lunar Sample Return Mission

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Martin Lo, Min-Kun ChungJPL

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

Lunar Sample Return Mission

MWL - 7

Martin Lo, Min-Kun ChungJPL

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

Lunar Sample Return Mission

MWL - 8

Martin Lo, Min-Kun ChungJPL

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

Lunar Sample Return Mission

MWL - 9

Martin Lo, Min-Kun ChungJPL

Case LL1 : 943 m/s Cheaper Than Conic

CaseT

(day)Total V

(m/s)

LL2 146 8586

LL1 151 8663

EL1 553 8160

Conic 23 9606•

LL1•

LL2

MoonEarth

• EL2

• EL1

Lunar Sample Return Mission

MWL - 10

Martin Lo, Min-Kun ChungJPL

Case EL1 : 1446 m/s Cheaper Than Conic

CaseT

(day)Total V

(m/s)

LL2 146 8586

LL1 151 8663

EL1 553 8160

Conic 23 9606•

LL1•

LL2

MoonEarth

• EL2

• EL1

Lunar Sample Return Mission

MWL - 11

Martin Lo, Min-Kun ChungJPL

LL2 Case: Direct Transfer to LL2 Lissajous Orbit

• Lunar Transfer

• LL2 Lissajous Orbit

• Lunar Landing

• Lander Return

EL1

Earth

Moon

EL2

LanderReturn

Lunar Sample Return Mission

MWL - 12

Martin Lo, Min-Kun ChungJPL

LL2 Case: Trans-Lunar Phase

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

Earth6/14/90

LanderReturn

LL1

LL2

Moon

LL2 Insertion570 m/s at 6/18/09

Lander Return

Earth11/7/90

Lunar Sample Return Mission

MWL - 13

Martin Lo, Min-Kun ChungJPL

LL2 Stable Manifold Insertion

LL1LL2

Moon

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

Lunar Sample Return Mission

MWL - 14

Martin Lo, Min-Kun ChungJPL

LL2 Case: Earth Moon Rotating Frame

EL1

Earth

Moon

EL2

LanderReturn

Lunar Sample Return Mission

MWL - 15

Martin Lo, Min-Kun ChungJPL

LanderReturn

Earth

Orbiter

LL2

LL1

LL2 Case: EME2000 Inertial Frame

Lunar Sample Return Mission

MWL - 16

Martin Lo, Min-Kun ChungJPL

LanderReturn

Earth

Orbiter

EL2

LL2

LL1

LL2 Case: Sun-Earth Rotating Frame

Lunar Sample Return Mission

MWL - 17

Martin Lo, Min-Kun ChungJPL

LL2 Case: Mission Sequence & V’s

Mission SequenceDate

(2009)T

(days)

Combo V

(m/s)

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

Lunar Sample Return Mission

MWL - 18

Martin Lo, Min-Kun ChungJPL

MoonLL1LL2

Heteroclinic Connection

LL1 Case: LL2 via LL1

• Insert into LL1 Stable Manifold

• Heteroclinic Connection for Comm. Orbiter

• Lunar Landing from LL1

Moon

LL1

Lander Departs for Moon: 95 m/s

Landing: 2330 m/s8.5 days later

Lunar Sample Return Mission

MWL - 19

Martin Lo, Min-Kun ChungJPL

LL1 Case: Mission Sequence & V’s

Mission SequenceDate

(2009)T

(days)Combo V (m/s)

Lander V (m/s)

Orbiter V (m/s)

Translunar Injection 6/9 0 3100

LL1 Halo Insertion 6/14 5 600

Orbiter LL1 Departure 6/19 10 14

Orbiter LL2 Arrival 7/7 28 0

Lander LL1 Departure 7/10 31 95

Lander Landing 7/16 37 2330

Lander Liftoff 7/28 49 2424

Earth Return 11/7 151

Navigation 25 50 25

V Total 3725 4899 39

LL2 Case

Lunar Sample Return Mission

MWL - 20

Martin Lo, Min-Kun ChungJPL

EL2

EL1 Case: LL2 via Earth L1

EL1

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

Lunar Sample Return Mission

MWL - 21

Martin Lo, Min-Kun ChungJPL

EL1 Case: Mission Sequence & V’s

Mission SequenceDate

(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

Lander LL2 Departure 7/7 403 35

Lander Landing 7/17 413 2335

Lander Liftoff 7/28 424 2424

Earth Return 11/7 553

Navigation 25 50 25

V Total 3291 4844 25

Reduction by Order of Magnotide

LL2 Case

Lunar Sample Return Mission

MWL - 22

Martin Lo, Min-Kun ChungJPL

• 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)

Lunar Sample Return Mission

MWL - 23

Martin Lo, Min-Kun ChungJPL

Mission SequenceDate

(2009)T

(days)Combo V (m/s)

Lander V (m/s)

Orbiter V (m/s)

Translunar Injection 7/16 0 3100

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)

Lunar Sample Return Mission

MWL - 24

Martin Lo, Min-Kun ChungJPL

Libration Point Mission Lowers V

• Saves Up to 1446 m/s!

• Provides Continuous Communication

• Trade V for Time

CaseT

(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

Lunar Sample Return Mission

MWL - 25

Martin Lo, Min-Kun ChungJPL

END

• END

Lunar Sample Return Mission

MWL - 26

Martin Lo, Min-Kun ChungJPL

Earth

Moon

LL1

Lissajous Orbit

LL1 Stable Manifold

LL1 Case: LL2 via LL1

• Insert into LL1 Stable Manifold

• Heteroclinic Connection for Comm. Orbiter

• Lunar Landing from LL1

Lunar Sample Return Mission

MWL - 27

Martin Lo, Min-Kun ChungJPL

MoonLL1 LL2

Heteroclinic Connection

LL1 Case: LL2 via LL1

• Insert into LL1 Stable Manifold

• Heteroclinic Connection for Comm. Orbiter

• Lunar Landing from LL1

Lunar Sample Return Mission

MWL - 28

Martin Lo, Min-Kun ChungJPL

Moon

LL1

Lander Departs for Moon: 95 m/s

Landing: 2330 m/s8.5 days later

LL1 Case: LL2 via LL1

• Insert into LL1 Stable Manifold

• Heteroclinic Connection for Comm. Orbiter

• Lunar Landing from LL1

Lunar Sample Return Mission

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

EARTH L2 HALO ORBIT

MOON

LUNAR L1 HALO ORBIT

LUNAR L2 HALO ORBIT

LUNAR L1 GATEWAY

Lunar Sample Return Mission

MWL - 30

Martin Lo, Min-Kun ChungJPL

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

Lunar Sample Return Mission

MWL - 31

Martin Lo, Min-Kun ChungJPL

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

Lunar Sample Return Mission

MWL - 32

Martin Lo, Min-Kun ChungJPL

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