Optimal low-thrust/invariant manifold Earth Moon transfer trajectories

Christopher S. Martin, Bruce A Conway

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Minimum-time and hence minimum-fuel trajectories are found for a spacecraft using continuous low-thrust propulsion to leave geosynchronous transfer orbit and enter a low-lunar orbit, transiting via the stable and unstable manifolds of a periodic orbit about the interior Earth-Moon Lagrange point. The optimizer chooses the thrust pointing angle time history, the points of arrival/departure from the stable and unstable manifold respectively and the size of the halo orbits, in order to minimize the powered flight time. The arrival position and velocity matching conditions are obtained from a parameterization of the orbit using cubic splines since no analytic description of the manifolds exist.

Original languageEnglish (US)
Title of host publicationSpaceflight Mechanics 2010 - Advances in the Astronautical Sciences
Subtitle of host publicationProceedings of the AAS/AIAA Space Flight Mechanics Meeting
Pages89-106
Number of pages18
StatePublished - Dec 1 2010
EventAAS/AIAA Space Flight Mechanics Meeting - San Diego, CA, United States
Duration: Feb 14 2010Feb 17 2010

Publication series

NameAdvances in the Astronautical Sciences
Volume136
ISSN (Print)0065-3438

Other

OtherAAS/AIAA Space Flight Mechanics Meeting
CountryUnited States
CitySan Diego, CA
Period2/14/102/17/10

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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