JPL Technical Report Server

The NASA Phoenix 2007 Mars Lander thruster calibration estimator: design and validation

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dc.contributor.author Lisano, Michael E.
dc.contributor.author Kruizinga, Gerhard L.
dc.contributor.author Portock, Brian
dc.date.accessioned 2015-07-14T18:00:47Z
dc.date.available 2015-07-14T18:00:47Z
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 08-2361
dc.identifier.uri http://hdl.handle.net/2014/45405
dc.description.abstract The NASA Phoenix 2007 Mars Lander mission, launched in August 2007 on its mission to land near the north pole of Mars in May 2008, had a driving need for entry-corridor delivery precision, which parlayed into stringent requirements on deep space navigation accuracy. This, in turn, necessitated in-cruise calibration of the three-axis thrust force vectors produced by each of the vehicle’s four reactioncontrol system (RCS) thrusters during frequent daily low-catalyst-bed-temperature firings done to maintain the 3-axis attitude deadbands. A novel recursive sigmapoint consider-covariance filter was designed, validated and ultimately utilized extensively during flight operations, to estimate the RCS force vectors, per individual thruster. The estimate was achieved through ground-based processing of Deep Space Network (DSN) and telemetered gyroscope data from the spacecraft’s inertial measurement unit (IMU), using a novel sigma-point consider filter (SPCF) formulation. During early-cruise active calibration, the spacecraft was flown in attitudes chosen, using this filter, to maximize observability of all thruster axes, to an extent constrained by vehicle thermal and communication considerations. The design of the Phoenix thruster calibration filter, and its validation through processing of archived Mars Odyssey thruster calibration radiometric data, and simulated sets of data, are discussed in this paper. The paper concludes with the formulation of the thruster calibration campaign and a summary of the thruster calibration campaign results. The SPCF algorithm is summarized in the Appendix. 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.subject EDL en_US
dc.subject small force en_US
dc.subject sigma-point filter en_US
dc.title The NASA Phoenix 2007 Mars Lander thruster calibration estimator: design and validation en_US
dc.type Preprint en_US


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