On the stability of displaced two-body lunar orbits

Jules Simo, Colin R. McInnes

Research output: Contribution to conferencePaper

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.
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

Fingerprint

Orbits
Moon
Earth (planet)

Keywords

  • orbits
  • space craft
  • space flight

Cite this

Simo, J., & McInnes, C. R. (2010). On the stability of displaced two-body lunar orbits. 1-10. Paper presented at 20th AIAA Space Flight Mechanics Meeting, San Diego, California, .
Simo, Jules ; McInnes, Colin R. / On the stability of displaced two-body lunar orbits. Paper presented at 20th AIAA Space Flight Mechanics Meeting, San Diego, California, .10 p.
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Simo, J & McInnes, CR 2010, 'On the stability of displaced two-body lunar orbits' Paper presented at 20th AIAA Space Flight Mechanics Meeting, San Diego, California, 14/02/10 - 17/02/10, pp. 1-10.

On the stability of displaced two-body lunar orbits. / Simo, Jules; McInnes, Colin R.

2010. 1-10 Paper presented at 20th AIAA Space Flight Mechanics Meeting, San Diego, California, .

Research output: Contribution to conferencePaper

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AU - McInnes, Colin R.

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N2 - 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.

AB - 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.

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Simo J, McInnes CR. On the stability of displaced two-body lunar orbits. 2010. Paper presented at 20th AIAA Space Flight Mechanics Meeting, San Diego, California, .