On the stability of displaced two-body lunar orbits

Jules Simo, Colin R. McInnes

Research output: Contribution to conferencePaper

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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 L1 and L2 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
Pages1-10
Number of pages10
Publication statusPublished - Feb 2010
Event20th AIAA Space Flight Mechanics Meeting - San Diego, California
Duration: 14 Feb 201017 Feb 2010

Conference

Conference20th AIAA Space Flight Mechanics Meeting
CitySan Diego, California
Period14/02/1017/02/10

Keywords

  • orbits
  • space craft
  • space flight

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