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Contingency trajectory design for a lunar orbit insertion maneuver failure by the ladee spacecraft
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Genova, A. L. |
| Copyright Year | 2014 |
| Description | This paper presents results from a contingency trajectory analysis performed for the Lunar Atmosphere & Dust Environment Explorer (LADEE) mission in the event of a missed lunar-orbit insertion (LOI) maneuver by the LADEE spacecraft. The effects of varying solar perturbations in the vicinity of the weak stability boundary (WSB) in the Sun-Earth system on the trajectory design are analyzed and discussed. It is shown that geocentric recovery trajectory options existed for the LADEE spacecraft, depending on the spacecraft's recovery time to perform an Earth escape-prevention maneuver after the hypothetical LOI maneuver failure and subsequent path traveled through the Sun-Earth WSB. If Earth-escape occurred, a heliocentric recovery option existed, but with reduced science capacapability for the spacecraft in an eccentric, not circular near-equatorial retrograde lunar orbit. |
| File Size | 256516 |
| Page Count | 6 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20150000695 |
| Archival Resource Key | ark:/13960/t7pp43k25 |
| Language | English |
| Publisher Date | 2014-08-04 |
| Access Restriction | Open |
| Subject Keyword | Ladee Missed Loi Contingency Rescue Operations Dust Explorer Satellites Lunar Atmosphere Lunar Orbits Orbit Insertion Trajectory Analysis Solar Orbits Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
