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 language | English |
|---|---|
| Pages | 1-10 |
| Number of pages | 10 |
| Publication status | Published - Feb 2010 |
| Event | 20th AIAA Space Flight Mechanics Meeting - San Diego, California Duration: 14 Feb 2010 → 17 Feb 2010 |
Conference
| Conference | 20th AIAA Space Flight Mechanics Meeting |
|---|---|
| City | San Diego, California |
| Period | 14/02/10 → 17/02/10 |
Keywords
- orbits
- space craft
- space flight