On the stability of approximate displaced lunar orbits

Jules Simo, Colin McInnes

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

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Abstract

In a prior study, a methodology was developed for computing approximate large displaced orbits in the Earth-Moon circular restricted three-body problem (CRTBP) by the Moon-Sail two-body problem. It was found that far from the L(1) and L(2) points, the approximate two-body analysis for large accelerations matches well with the dynamics of displaced orbits in relation to the three-body problem. In the present study, the linear stability characteristics of the families of approximate periodic orbits are investigated.
Original languageEnglish
Title of host publicationSpaceflight mechanics 2010
Subtitle of host publicationPTS I-III
EditorsD. Mortari, T.F. Starchville, A.J. Trask, J.K. Miller
Place of PublicationSan Diego, California
Pages1229-1238
Number of pages10
Publication statusPublished - 14 Feb 2010
Event20th Spaceflight Mechanics Meeting, Spaceflight Mechanics 2010 - San Diego, California, , United States
Duration: 14 Feb 2011 → 17 Feb 2011

Publication series

NameAdvances in the Astronautical Sciences
PublisherUnivelt Inc
Number1-3
Volume136
ISSN (Print)1081-6003

Conference

Conference20th Spaceflight Mechanics Meeting, Spaceflight Mechanics 2010
CountryUnited States
CitySan Diego, California,
Period14/02/11 → 17/02/11

Keywords

  • restricted 3-body problem
  • points
  • periodic-orbits
  • solar-sail

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