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Orbit determination for the 2007 Mars Phoenix Lander

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dc.contributor.author Ryne, Mark S.
dc.contributor.author Graat, Eric
dc.contributor.author Haw, Robert
dc.contributor.author Kruizinga, Gerhard
dc.contributor.author Lau, Eunice
dc.contributor.author Martin-Mur, Tomas
dc.contributor.author McElrath, Timothy
dc.contributor.author Nandi, Sumita
dc.contributor.author Portock9, Brian
dc.date.accessioned 2015-07-14T18:02:35Z
dc.date.available 2015-07-14T18:02:35Z
dc.date.issued 2008-08-18
dc.identifier.citation AIAA/AAS Astrodynamics Specialist Conference, Honolulu, Hawaii, August 18-21, 2008 en_US
dc.identifier.clearanceno 08-2794
dc.identifier.uri http://hdl.handle.net/2014/45419
dc.description.abstract The Phoenix mission is designed to study the arctic region of Mars. To achieve this goal, the spacecraft must be delivered to a narrow corridor at the top of the Martian atmosphere, which is approximately 20 km wide. This paper will discuss the details of the Phoenix orbit determination process and the effort to reduce errors below the level necessary to achieve successful atmospheric entry at Mars. Emphasis will be placed on properly modeling forces that perturb the spacecraft trajectory and the errors and uncertainties associated with those forces. Orbit determination covariance analysis strongly influenced mission operations scenarios, which were chosen to minimize errors and associated uncertainties. 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, 2008 en_US
dc.title Orbit determination for the 2007 Mars Phoenix Lander en_US
dc.type Preprint en_US


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