GPS/Magnetometer Based Satellite Navigation and Attitude Determination

Julie Deutschmann Thiene, Richard R. Harman and Itzhack Y. Bar-Itzhack

Abstract:	This work presents the development and testing of a unified navigation algorithm that produces estimates of attitude, angular rate, position, and velocity for a low earth orbit (LEO) spacecraft. The system relies on GPS phase and range data as well as magnetometer data. The algorithm used is an extended Kalman filter (EKF), blended with a pseudo-linear Kalman filter algorithm. This combined algorithm that was developed to provide LEO attitude, orbit, and rate estimates using magnetometer and sun sensor data is modified to use GPS rather than sun sensor data. Simulations that were carried out prove that when incorporating a two state receiver clock bias error and using measurements from two GPS space vehicles (SVs), the system is observable, and thus is estimable, and yields very good results.
Published in:	Proceedings of the 14th International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 2001) September 11 - 14, 2001 Salt Palace Convention Center Salt Lake City, UT
Pages:	2946 - 2951
Cite this article:	Thiene, Julie Deutschmann, Harman, Richard R., Bar-Itzhack, Itzhack Y., "GPS/Magnetometer Based Satellite Navigation and Attitude Determination," Proceedings of the 14th International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 2001), Salt Lake City, UT, September 2001, pp. 2946-2951.
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