GPS Relative Navigation for Space Vehicles

R. W. Okkes and R. Lucas

Abstract:	The paper investigates the application of GPS to assist in rendez-vous operations of two space vehicles, typically a Columbus free flying element and the International Space Station (ISS) or the ESA spaceplane Hermes and a Columbus element or ISS. The two space vehicles involved in rendez-vous are considered to be equipped with GPS terminals for the purpose of performing their own absolute navigation. Rendez-vous operations require accurate determination of relative position an velocity to enable precise prediction of state vector data at a predefined "homing point", located in the vicinity of the target vehicle to be reached by maneuvering the chaser space vehicle. Relative state vector data may be determined by essentially two ways: a) by differencing the absolute ·navigation estimates of the two rendez-vous vehicles, referenced to common (GPS) time; b) by processing (Kalman filtering) differenced pseudo range data, differenced· carrier phase measurements and additional auxiliary data (such as attitude, inertial measurement unit data and timing). The paper describes the characteristics of the GPS measurement data for relative state vector determination and the implementation of a suitable Kalman filter for use on board the rendez-vous space vehicles or for flight simulation.
Published in:	Proceedings of the International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 1988) September 19 - 23, 1988 The Broadmoor Hotel Colorado Spring, CO
Pages:	89 - 93
Cite this article:	Okkes, R. W., Lucas, R., "GPS Relative Navigation for Space Vehicles," Proceedings of the International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 1988), Colorado Spring, CO, September 1988, pp. 89-93.
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