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Trajectory Design for the Lunar Polar Hydrogen Mapper MissionThe presented trajectory was designed for the Lunar Polar Hydrogen Mapper (LunaH-Map) 6U CubeSat, which was awarded a ride on NASAs Space Launch System (SLS) with Exploration Mission 1 (EM-1) via NASAs 2015 SIMPLEX proposal call. After deployment from EM-1s upper stage (which is planned to enter heliocentric space via a lunar flyby), the LunaH-Map CubeSat will alter its trajectory via its low-thrust ion engine to target a lunar flyby that yields a Sun-Earth-Moon weak stability boundary transfer to set up a ballistic lunar capture. Finally, the orbit energy is lowered to reach the required quasi-frozen science orbit with periselene above the lunar south pole.
Document ID
20170009830
Document Type
Conference Paper
Authors
Genova, Anthony L. (NASA Ames Research Center Moffett Field, CA, United States)
Dunham, David W. (KinetX Aerospace, Inc. Greenbelt, MD, United States)
Date Acquired
October 11, 2017
Publication Date
February 5, 2017
Subject Category
Astrodynamics
Lunar and Planetary Science and Exploration
Report/Patent Number
ARC-E-DAA-TN39796
AAS 17-456
Meeting Information
AAS/AIAA Space Flight Mechanics Meeting(San Antonio, TX)
Funding Number(s)
CONTRACT_GRANT: NNG10CP02C
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
lunar polar orbit
ballistic capture
cubesat

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