Genesis Orals template

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Lunar Sample Return via the Interplanetary
Supherhighway
Lunar Orbit
AIAA/AAS Astrodynamics Specilaist
Conference Martin.Lo_at_jpl.nasa.gov Min-Kun.Chung_at_jp
l.nasa.gov
JPL Caltech
8/6/2002
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Agenda

• Lunar Sample Return Mission Overview
• Baseline Mission Scenario
• Lunar L2 Case (LL2)
• Mission Performance Comparison

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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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Key Results

• Metric Total DV of
• Combo
• Lander/Return Module
• Communications Orbiter
• Trade Time for Total DV
• Best Case 1446 m/s Less than Conic Case
• Baseline 1020 m/s Less than Conic Case

Case DT (days) Total DV (m/s) -Conic DV (m/s)
LL2 146 8586 1020
LL1 151 8663 943
EL1 553 8160 1446
Conic 23 9606 0
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(No Transcript)
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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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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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Case LL2 1020 m/s Cheaper Than Conic
BASELINE CASE
Case DT (day) Total DV (m/s)
LL2 146 8586
LL1 151 8663
EL1 553 8160
Conic 23 9606
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Case LL1 943 m/s Cheaper Than Conic
Case DT (day) Total DV (m/s)
LL2 146 8586
LL1 151 8663
EL1 553 8160
Conic 23 9606
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Case EL1 1446 m/s Cheaper Than Conic
Case DT (day) Total DV (m/s)
LL2 146 8586
LL1 151 8663
EL1 553 8160
Conic 23 9606
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LL2 Case Direct Transfer to LL2 Lissajous Orbit

• Lunar Transfer
• LL2 Lissajous Orbit
• Lunar Landing
• Lander Return

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LL2 Case Trans-Lunar Phase
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LL2 Case Lunar Phase
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LL2 Case Earth Moon Rotating Frame
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LL2 Case EME2000 Inertial Frame
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LL2 Case Sun-Earth Rotating Frame
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LL2 Case Mission Sequence DVs
Mission Sequence Date (2009) DT (days) Combo DV (m/s) Lander DV (m/s) Orbiter DV (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
DV Total 3717 4844 25
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LL1 Case LL2 via LL1

• Insert into LL1 Stable Manifold
• Heteroclinic Connection for Comm. Orbiter
• Lunar Landing from LL1

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LL1 Case Mission Sequence DVs
Mission Sequence Date (2009) DT (days) Combo DV (m/s) Lander DV (m/s) Orbiter DV (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
DV Total 3725 4899 39
LL2 Case
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EL1 Case LL2 via Earth L1

• Reduce LL2 LOI DV Launch to EL1 Fall to LL2
• Once There, Follows LL2 Case

FAIR/DART Trajctory
EL2
EL1
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EL1 Case Mission Sequence DVs
Mission Sequence Date (2009) DT (days) Combo DV (m/s) Lander DV (m/s) Orbiter DV (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
DV Total 3291 4844 25
Reduction by Order of Magnotide
LL2 Case
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Conic Case (S. Williams, JPL)

• Conic Trans-Lunar Orbit
• Lander in 100-km Lunar Parking Orbit
• Orbiter in Highly Elliptical Orbit
• 100x8700 km, 12 hr Period

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Conic Case (S. Williams, JPL)
Mission Sequence Date (2009) DT (days) Combo DV (m/s) Lander DV (m/s) Orbiter DV (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
DV Total 3125 5975 506
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Libration Point Mission Lowers DV

• Saves Up to 1446 m/s!
• Provides Continuous Communication
• Trade DV for Time

Case DT (days) ComboDV (m/s) Lander DV (m/s) Orbiter DV (m/s) Total DV (m/s) -Conic DV (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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END

• END

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LL1 Case LL2 via LL1

• Insert into LL1 Stable Manifold
• Heteroclinic Connection for Comm. Orbiter
• Lunar Landing from LL1

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LL1 Case LL2 via LL1

• Insert into LL1 Stable Manifold
• Heteroclinic Connection for Comm. Orbiter
• Lunar Landing from LL1

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LL1 Case LL2 via LL1

• Insert into LL1 Stable Manifold
• Heteroclinic Connection for Comm. Orbiter
• Lunar Landing from LL1

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Interplanetary Superhighway in the Earths
Neighborhood

• Collection of Invariant Manifolds of
  Quasiperiodic Orbits in the Solar System
• Coupled Three Body Systems

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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

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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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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