Part of the Space Mathematics Division in CNES, the Flight Dynamics Center provides attitude and orbit determinations and maneuvers during the Launch and Early Operation Phase (LEOP) of geostationary satellites. Orbit determination is based on a Kalman filter method; when the 2 GHz CNES/NASA network is used, Doppler measurements are available and allow orbit determination during the apogee maneuvers. This method was used for TELE-X and TDF 2 LEOP (3-axis controlled satellites) and also for TELECOM 2 and HISPASAT (spun satellites): it enables us to follow the evolution of the maneuver and gives out a quite accurate estimation of the reached orbit. In this paper, we briefly describe the dynamic models of the orbit evolution in both cases, '3-axis' and 'inertial' thrust. Then, we present the results obtained for each case. Afterwards, we present some cases to show the robustness of the filter.
Kalman Filtering Applied to Real-Time Monitoring of Apogee Maneuvers
1993
6 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Astronautics , Apogees , Ground based control , Orbit calculation , Satellite control , Satellite ground support , Spacecraft maneuvers , Kalman filters , Real time operation , Geosynchronous orbits , Satellite attitude control , Satellite orbits , Synchronous platforms , Foreign technology
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