Publication Date:
2019-07-13
Description:
This 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.
Keywords:
Astrodynamics
Type:
GSFC-E-DAA-TN30224
,
International Conference on Astrodynamics Tools and Techniques; Mar 14, 2016 - Mar 17, 2016; Darmstadt; Germany
Format:
application/pdf
