GPS Attitude Determination for Microsatellites

S. Purivigraipong, Y. Hashida

Abstract:	This paper presents an approach to single short baseline GPS (Global Positioning System) attitude determination for small satellite applications in low Earth orbit. A new technique to estimate path difference in the presence of an integer cycle slip due to measurement error is described. A new algorithm based on the recursive least squares (RLS) technique to estimate line bias is implemented. An estimation algorithm based on the extended Kalman filter is developed to estimate spacecraft attitude. An integrity check for filtering is implemented to prevent divergence or large error. The robustness of the filtering estimator is tested with simulated anomalous conditions. A gravity gradient stabilised/nadir pointing spacecraft accommo-dated with 30 cm baseline length is assumed in this re-search.
Published in:	Proceedings of the 12th International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 1999) September 14 - 17, 1999 Nashville, TN
Pages:	2017 - 2026
Cite this article:	Purivigraipong, S., Hashida, Y., "GPS Attitude Determination for Microsatellites," Proceedings of the 12th International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 1999), Nashville, TN, September 1999, pp. 2017-2026.
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