Study Of The Method Of Orbit Determination For Geostationary (GEO) Satellite In Case Of Maneuvers

Statistical orbit determination with high precision relies on not only the observation with high precision, but also the dynamic model with high precision. As it's difficult to model maneuver power, the dynamic statistics orbit determination doesn't work effectively during and after the long time period of maneuver, China second generation satellite navigation system constitutes of GEO, IGSO and MEO satellites, and GEO satellite's maneuver is more frequent. It's a very important issue that how to reduce the impact from satellite maneuver, to obtain the orbit with high precision in case of maneuvers, and to improve navigation satellite ephemeris availability.In this paper, the method of maneuver monitor and that of orbit determination in case of maneuvers are studied, the main research work includes:1. The method of maneuver monitoring of GEO satellite is studied. GEO satellite maneuver monitoring using the observation of the orbit measurement system with transponder is achieved. The actual experiment was done based on the observation of'SINO-1'satellite. The results show that the time difference between the detected maneuver time (including the start and end time) obtained with the method presented and the true maneuver time (provided by the satellite company) is less than two minutes, the monitoring of maneuver is helpful to switch methods of orbit determination in case of maneuver.2. The issue of orbit determination are solved using of semi-geometric -dynamics in some extent during and after maneuver. The difference (RMS) of orbit determination between orbit determination of semi-geometric -dynamics and dynamics method is no more than ten meters after the satellite's maneuvers.