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Low-Thrust Transfers from Distant Retrograde Orbits to L2 Halo Orbits in the Earth-Moon SystemThis paper presents a study of transfers between distant retrograde orbits (DROs) and L2 halo orbits in the Earth-Moon system that could be flown by a spacecraft with solar electric propulsion (SEP). Two collocation-based optimal control methods are used to optimize these highly-nonlinear transfers: Legendre pseudospectral and Hermite-Simpson. Transfers between DROs and halo orbits using low-thrust propulsion have not been studied previously. This paper offers a study of several families of trajectories, parameterized by the number of orbital revolutions in a synodic frame. Even with a poor initial guess, a method is described to reliably generate families of solutions. The circular restricted 3-body problem (CRTBP) is used throughout the paper so that the results are autonomous and simpler to understand.
Document ID
20160003314
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Parrish, Nathan L. (Colorado Univ. Boulder, CO, United States)
Parker, Jeffrey S. (Colorado Univ. Boulder, CO, United States)
Hughes, Steven P. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Heiligers, Jeannette (Delft Univ. of Technology Delft, Netherlands)
Date Acquired
March 11, 2016
Publication Date
March 14, 2016
Subject Category
Astrodynamics
Report/Patent Number
GSFC-E-DAA-TN30224
Meeting Information
Meeting: International Conference on Astrodynamics Tools and Techniques
Location: Darmstadt
Country: Germany
Start Date: March 14, 2016
End Date: March 17, 2016
Sponsors: European Space Agency
Funding Number(s)
CONTRACT_GRANT: NNX15AR54H
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
trajectory design
optimization
critical design

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