Real-Time Sequential Orbit Determination for LEO Satellites via Kalman Filtering Of GPS Data

P. Tortora and F. Graziani

Abstract:	A method is presented for fast estimation of the mean orbital elements of a Low Earth Orbiting satellite using data from a GPS receiver. The algorithm has a recursive structure and is mainly based on a pre-filtering procedure, where instantaneous position and velocity solutions are improved, and on a Recursive Least Square estimator, where the mean orbital elements are determined, using, as an input, the instantaneous osculating orbital elements. Useful as an autonomous way to supply the mean orbital parameters to an automated ground station, this algorithm has low computational and data storage requirements, along with an high achievable accuracy. These characteristics render this method suitable for low-cost microsatellites, where computing time is a central issue, as well as on satellites with more stringent needs in terms of position determination accuracy.
Published in:	Proceedings of the IAIN World Congress and the 56th Annual Meeting of The Institute of Navigation (2000) June 26 - 28, 2000 The Catamaran Resort Hotel San Diego, CA
Pages:	481 - 488
Cite this article:	Tortora, P., Graziani, F., "Real-Time Sequential Orbit Determination for LEO Satellites via Kalman Filtering Of GPS Data," Proceedings of the IAIN World Congress and the 56th Annual Meeting of The Institute of Navigation (2000), San Diego, CA, June 2000, pp. 481-488.
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