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Trajectory design for the Mars Reconnaissance Orbiter Mission

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dc.contributor.author Halsell, C. A. en_US
dc.contributor.author Bowes, A. en_US
dc.contributor.author Lyons, D. T. en_US
dc.contributor.author Johnston, M. D. en_US
dc.contributor.author Lock, R. E. en_US
dc.contributor.author Xaypraseuth, P. en_US
dc.contributor.author Bhaskaran, S. en_US
dc.contributor.author Highsmith, D. E. en_US
dc.contributor.author Jab, M. K. en_US
dc.date.accessioned 2004-09-17T18:40:35Z
dc.date.available 2004-09-17T18:40:35Z
dc.date.issued 2002-02-09 en_US
dc.identifier.citation 13th Annual AAS/AIAA Space Flight Mechanics Meeting en_US
dc.identifier.citation Ponce, Puerto Rico, USA en_US
dc.identifier.clearanceno 02-2385 en_US
dc.identifier.uri http://hdl.handle.net/2014/10412
dc.description.abstract This paper describes the analysis and design evolution of the Mars Reconnaissance Orbiter trajectory from launch to end-of-mission. The mission uses a combination of propulsive maneuvers and aerobraking techniques to deliver the orbiter to a low-altitude frozen orbit at Mars. The launch/arrival space for the 2005 Earth-Mars opportunity will be described as well as the particular launch strategy chosen for this mission. Details of the aerobraking profile will be provided. Finally, the Primary Science Orbit will be examined, and the trade-offs between science objectives and orbiter capability will be presented. en_US
dc.format.extent 2908499 bytes
dc.format.mimetype application/pdf
dc.language.iso en_US
dc.subject.other Mars Reconnaissance Orbiter trajectory Mars MRO en_US
dc.title Trajectory design for the Mars Reconnaissance Orbiter Mission en_US


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