Stabilization of Low Orbiting Spacecraft Using GPS

Barry A. Stein and Wai L. Tsang

Abstract:	The determination of attitude for an orbiting spacecraft is of obvious importance. Usual techniques such as utilizing inertial guidance components are, however, fairly expensive especially if high accuracies are required for the mission. It is the purpose of this paper to explore a lower cost alternative yielding equal or better accuracies, reliability, and repeatability. The approach under consideration utilizes the Global Positioning System (GPS) with multiple antennas for one or more receivers spaced appropriately on the outer surface of the spacecraft. Several interconnected variables are studied in order to evaluated accuracy, reliability, repeatability and symmetry. The latter is useful when attempting to minimize calculations and processing time. These variables include orbital parameters such as altitude, eccentricity, inclination, and satellite spacing as well as various time factors. Special consideration has been given to LEOSAT/LlGHTSAT types of satellites and orbits due to the high interest in these low-cost, low-orbit systems. It has been demonstrated by simulation that satellite attitude determination using GPS is indeed feasible, practical, and cost effective for a variety of missions. Also discussed are alternative ways to determine attitude for these cases using either modified or aided GPS techniques. Results for all of the above scenarios are presented in both tabular and graphic form.
Published in:	Proceedings of the 47th Annual Meeting of The Institute of Navigation (1991) June 10 - 12, 1991 Williamsburg Hilton and National Conference Center Williamsburg, VA
Pages:	5 - 7
Cite this article:	Stein, Barry A., Tsang, Wai L., "Stabilization of Low Orbiting Spacecraft Using GPS," Proceedings of the 47th Annual Meeting of The Institute of Navigation (1991), Williamsburg, VA, June 1991, pp. 5-7.
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