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Orbital transfer techniques for round-trip Mars missions

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dc.contributor.author Landau, Damon
dc.date.accessioned 2014-02-26T21:14:16Z
dc.date.available 2014-02-26T21:14:16Z
dc.date.issued 2013-02-11
dc.identifier.citation 23rd AAS/AIAA Spaceflight Mechanics Meeting, Kauai, Hawaii, February 10-14 2013 en_US
dc.identifier.clearanceno 13-0752
dc.identifier.uri http://hdl.handle.net/2014/44352
dc.description.abstract 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. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2013 en_US
dc.subject human missions en_US
dc.subject Interplanetary trajectories en_US
dc.title Orbital transfer techniques for round-trip Mars missions en_US
dc.type Preprint en_US


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