Autonomous Integrated GPS/CES/SS Navigation for High-Altitude Orbits

Jorge I. Galdos, Triveni N. Upadhyay, Anil Kumar, Bin Wu, James J. Lomas, Raymond A. French

Abstract:	This paper develops an approach to achieving au- tonomous, fault-tolerant spacecraft navigation at high Earth orbits with apogees of 100,000 km. The ap- proach is based on integrating measurements pro vided by a Global Positioning System (GPS) receiver, conical Earth sensors (CES), and Sun/Moon sensors (SMS). Integration algorithms are developed to com- bine measurements from the three sensors. Monte Carlo simulations show that GPS can be used stan- dalone to navigate at these orbits, but that signifi- cant accuracy improvements over the individual sen- sors are achieved by integrating the three sensors.
Published in:	Proceedings of the 1994 National Technical Meeting of The Institute of Navigation January 24 - 26, 1994 Catamaran Resort Hotel San Diego, CA
Pages:	381 - 392
Cite this article:	Galdos, Jorge I., Upadhyay, Triveni N., Kumar, Anil, Wu, Bin, Lomas, James J., French, Raymond A., "Autonomous Integrated GPS/CES/SS Navigation for High-Altitude Orbits," Proceedings of the 1994 National Technical Meeting of The Institute of Navigation, San Diego, CA, January 1994, pp. 381-392.
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