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dc.contributor.advisorCristi, Roberto
dc.contributor.advisorAgrawal, Brij
dc.contributor.authorWatson, Vincent C.
dc.dateDecember 2003
dc.date.accessioned2012-03-14T17:47:49Z
dc.date.available2012-03-14T17:47:49Z
dc.date.issued2003-12
dc.description.abstractSpacecraft attitude estimation and pointing accuracy have always been limited by imperfect sensors. The rate gyroscope is one of the most critical instruments used in spacecraft attitude estimation and unfortunately historical trends show this instrument degrades significantly with time. Degraded rate gyroscopes have impacted the missions for several NASA and ESA spacecraft, including the Hubble Telescope. A possible solution to this problem is using a mathematically modeled dynamic gyroscope in lieu of a real one. In this thesis, data from such a gyro is presented and integrated into a spacecraft attitude estimation algorithm. The impediment to spacecraft attitude estimation presented by imperfect sensors has been overcome by developing more accurate sensors and using Kalman filters to reduce the effect of noisy measurements. Kalman filters for spacecraft attitude estimation have historically been based on an Euler angle or quaternion formulation. Though Euler angles and quaternions are arguably the easiest methods with which to describe the attitude of a spacecraft, other methods of describing attitudes do exist - including the Gibbs and Rodriguez parameters. A Kalman filter based upon the Gibbs parameter is presented and analyzed in this thesis.en_US
dc.description.urihttp://archive.org/details/angularrateestim109456118
dc.format.extentxiii, 55 p. : col. ill.en_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshArtificial satellitesen_US
dc.subject.lcshAttitudeen_US
dc.subject.lcshKalman filteringen_US
dc.subject.lcshGyroscopesen_US
dc.titleAngular rate estimation by multiplicative Kalman filtering techniquesen_US
dc.typeThesisen_US
dc.contributor.departmentMechanical and Astronautical Engineering
dc.subject.authorKalman filteren_US
dc.subject.authorGibbs parameteren_US
dc.subject.authorDynamic gyroscopeen_US
dc.subject.authorAttitude estimationen_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S. in Astronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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