GPS On-board System for Orbit Determination of CESAR Satellite

Janusz Zielinski, Pitor Fraczyk, Jan Kazmierski, Milena Rutkowska

Abstract:	The international mission CESAR (Central European Satellite for Advanced Research) is planned in frame of the Central European Initiative cooperation. CESAR will fly in an orbit with 400 km perigee, 1000 km apogee and 70” inclination. The spacecraft mass is about 300 kg, planned lifetime about two years. Tracking and orbit determination can be done with GPS date received by the on- board receiver which is under construction in laboratories of mentioned institutions in Poland. The system will permit the real time determination of the satellite state vector, the phase and frequency of the spacecraft rotation and will provide the time scale and frequency for board operations.
Published in:	Proceedings of the 7th International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 1994) September 20 - 23, 1994 Salt Palace Convention Center Salt Lake City, UT
Pages:	1263 - 1266
Cite this article:	Zielinski, Janusz, Fraczyk, Pitor, Kazmierski, Jan, Rutkowska, Milena, "GPS On-board System for Orbit Determination of CESAR Satellite," Proceedings of the 7th International Technical Meeting of the Satellite Division of The Institute of Navigation (ION GPS 1994), Salt Lake City, UT, September 1994, pp. 1263-1266.
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