Mars trajectory design options were examined that would accommodate a premature termination of a nominal manned opposition class mission for opportunities between 2010 and 2025. In this study, aborts that provided a minimum increase in the initial vehicle mass in low Earth orbit (IMLEO) were identified by locating direct transfer nominal missions and nominal missions including an outbound or inbound Venus swing-by that minimized IMLEO. The ease with which these missions could be aborted while meeting propulsion and time constraints was investigated by examining free return (unpowered) and powered aborts. Further reductions in trip time were made to some aborts by the addition or removal of an inbound Venus swing-by.
Abort Options for Potential Mars Missions
1994
8 pages
Report
No indication
English
Astronautics , Extraterrestrial Exploration , Abort trajectories , Aborted missions , Manned mars missions , Mars exploration , Mission planning , Orbit calculation , Design analysis , Mars sample return missions , Earth-mars trajectories , Flight time , Low earth orbits , Mars excursion module , Position (Location) , Swingby technique
Abort Options for Potential Mars Missions
NTRS | 1994
|Abort Options for Potential Mars Missions
Online Contents | 1994
|Abort options for potential Mars missions
AIAA | 1994
|