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

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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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(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
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Case LL1 943 m/s Cheaper Than Conic
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Case EL1 1446 m/s Cheaper Than Conic
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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
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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
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
Reduction by Order of Magnitude
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)
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Libration Point Mission Lowers DV

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

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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