Download - 8/6/2002
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8/6/2002
AIAA/AAS Astrodynamics Specilaist [email protected]
[email protected] 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
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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
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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)
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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
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Lunar Sample Return Mission
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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
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Lunar Sample Return Mission
MWL - 6
Martin Lo, Min-Kun ChungJPL
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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
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Lunar Sample Return Mission
MWL - 8
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
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Lunar Sample Return Mission
MWL - 9
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
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Lunar Sample Return Mission
MWL - 10
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
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Lunar Sample Return Mission
MWL - 11
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
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Lunar Sample Return Mission
MWL - 12
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
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Lunar Sample Return Mission
MWL - 13
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
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Lunar Sample Return Mission
MWL - 14
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
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Lunar Sample Return Mission
MWL - 15
Martin Lo, Min-Kun ChungJPL
LL2 Case: Earth Moon Rotating Frame
EL1
Earth
Moon
EL2
LanderReturn
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Lunar Sample Return Mission
MWL - 16
Martin Lo, Min-Kun ChungJPL
LanderReturn
Earth
Orbiter
LL2
LL1
LL2 Case: EME2000 Inertial Frame
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Lunar Sample Return Mission
MWL - 17
Martin Lo, Min-Kun ChungJPL
LanderReturn
Earth
Orbiter
EL2
LL2
LL1
LL2 Case: Sun-Earth Rotating Frame
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Lunar Sample Return Mission
MWL - 18
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
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Lunar Sample Return Mission
MWL - 19
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
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Lunar Sample Return Mission
MWL - 20
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
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Lunar Sample Return Mission
MWL - 21
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
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Lunar Sample Return Mission
MWL - 22
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 Magnitude
LL2 Case
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Lunar Sample Return Mission
MWL - 23
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)
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Lunar Sample Return Mission
MWL - 24
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)
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Lunar Sample Return Mission
MWL - 25
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
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Lunar Sample Return Mission
MWL - 26
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
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Lunar Sample Return Mission
MWL - 27
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