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Navigation challenges of the Mars Phoenix Lander mission

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dc.contributor.author Portock, Brian M.
dc.contributor.author Kruizinga, Gerhard
dc.contributor.author Bonfiglio, Eugene
dc.contributor.author Raofi, Behzad
dc.contributor.author Ryne, Mark
dc.date.accessioned 2015-07-14T17:56:31Z
dc.date.available 2015-07-14T17:56:31Z
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 08-2788
dc.identifier.uri http://hdl.handle.net/2014/45373
dc.description.abstract The Mars Phoenix Lander mission was launched on August 4th, 2007. To land safely at the desired landing location on the Mars surface, the spacecraft trajectory had to be controlled to a set of stringent atmospheric entry and landing conditions. The landing location needed to be controlled to an elliptical area with dimensions of 100km by 20km. The two corresponding critical components of the atmospheric entry conditions are the entry flight path angle (target: -13.0 deg ±0.21 deg) and the entry time (within ±30 seconds). The purpose of this paper is to describe the navigation strategies used to overcome the challenges posed during spacecraft operations, which included an attitude control thruster calibration campaign, a trajectory control strategy, and a trajectory reconstruction strategy. Overcoming the navigation challenges resulted in final Mars atmospheric entry conditions just 0.007 deg off in entry flight path angle and 14.9 sec early in entry time. These entry dispersions in addition to the entry, descent, and landing trajectory dispersion through the atmosphere, lead to a final landing location just 7 km away from the desired landing target. 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 Navigation challenges of the Mars Phoenix Lander mission en_US
dc.type Preprint en_US


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