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.
|Title of host publication||Spaceflight mechanics 2010|
|Subtitle of host publication||PTS I-III|
|Editors||D. Mortari, T.F. Starchville, A.J. Trask, J.K. Miller|
|Place of Publication||San Diego, California|
|Number of pages||10|
|Publication status||Published - 14 Feb 2010|
|Event||20th Spaceflight Mechanics Meeting, Spaceflight Mechanics 2010 - San Diego, California, , United States|
Duration: 14 Feb 2011 → 17 Feb 2011
|Name||Advances in the Astronautical Sciences|
|Conference||20th Spaceflight Mechanics Meeting, Spaceflight Mechanics 2010|
|City||San Diego, California,|
|Period||14/02/11 → 17/02/11|
- restricted 3-body problem
Simo, J., & McInnes, C. (2010). On the stability of approximate displaced lunar orbits. In D. Mortari, T. F. Starchville, A. J. Trask, & J. K. Miller (Eds.), Spaceflight mechanics 2010: PTS I-III (pp. 1229-1238). (Advances in the Astronautical Sciences; Vol. 136, No. 1-3). San Diego, California.