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Trajectory design for the Mars Reconnaissance Orbiter Mission

Show simple item record Halsell, C. A. en_US Bowes, A. en_US Lyons, D. T. en_US Johnston, M. D. en_US Lock, R. E. en_US Xaypraseuth, P. en_US Bhaskaran, S. en_US Highsmith, D. E. en_US Jab, M. K. en_US 2004-09-17T18:40:35Z 2004-09-17T18:40:35Z 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.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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