The human exploration of Phobos and Deimos or the retrieval of a surface sample launched to low-Mars orbit presents a highly constrained orbital transfer problem. In general, the plane of the target orbit will not be accessible from the arrival or departure interplanetary trajectories with an (energetically optimal) tangential burn at periapsis. The orbital design is further complicated by the addition of a high-energy parking orbit for the relatively massive Deep Space Vehicle to reduce propellant expenditure, while the crew transfers to and from the target orbit in a smaller Space Exploration Vehicle. The proposed strategy shifts the arrival and departure maneuvers away from periapsis so that the apsidal line of the parking orbit lies in the plane of the target orbit, permitting highly efficient plane change maneuvers at apoapsis of the elliptical parking orbit. An apsidal shift during the arrival or departure maneuver is approximately five times as efficient as maneuvering while in Mars orbit, thus significantly reducing the propellant necessary to transfer between the arrival, target, and departure orbits.
Orbital Transfer Techniques for Round-Trip Mars Missions
AAS/AIAA Spaceflight Mechanics Meeting ; 2013 ; Kauai, HI, United States
2013-02-10
Conference paper
No indication
English
Orbital Transfer Techniques for Round-Trip Mars Missions (AAS 13-449)
British Library Conference Proceedings | 2013
|Launch window analysis for round trip Mars missions
NTRS | 1967
|Launch Window Analysis for Round Trip MARS Missions
NTIS | 1967
|Launch window analysis for round trip Mars missions.
NTRS | 1968
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