Abstract
| Language | English |
|---|---|
| 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 |
| Pages | 1229-1238 |
| 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 |
Publication series
| Name | Advances in the Astronautical Sciences |
|---|---|
| Publisher | Univelt Inc |
| No. | 1-3 |
| Volume | 136 |
| ISSN (Print) | 1081-6003 |
Conference
| Conference | 20th Spaceflight Mechanics Meeting, Spaceflight Mechanics 2010 |
|---|---|
| Country | United States |
| City | San Diego, California, |
| Period | 14/02/11 → 17/02/11 |
Fingerprint
Keywords
- restricted 3-body problem
- points
- periodic-orbits
- solar-sail
Cite this
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On the stability of approximate displaced lunar orbits. / Simo, Jules; McInnes, Colin.
Spaceflight mechanics 2010: PTS I-III . ed. / D. Mortari; T.F. Starchville; A.J. Trask; J.K. Miller. San Diego, California, 2010. p. 1229-1238 (Advances in the Astronautical Sciences; Vol. 136, No. 1-3).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book
TY - GEN
T1 - On the stability of approximate displaced lunar orbits
AU - Simo, Jules
AU - McInnes, Colin
PY - 2010/2/14
Y1 - 2010/2/14
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 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.
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 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.
KW - restricted 3-body problem
KW - points
KW - periodic-orbits
KW - solar-sail
UR - http://www.space-flight.org/AAS_meetings/2010_winter/2010%20winter.html
M3 - Conference contribution book
SN - 9780877035602
T3 - Advances in the Astronautical Sciences
SP - 1229
EP - 1238
BT - Spaceflight mechanics 2010
A2 - Mortari, D.
A2 - Starchville, T.F.
A2 - Trask, A.J.
A2 - Miller, J.K.
CY - San Diego, California
ER -