Real-Time Orbit Determination of Geostationary Orbit Satellite Using GNSS Navigation Solution

The on-board orbit determination precision of geostationary orbit satellite based on orbit prediction results of on-ground is dependent on on-board orbit re-generation algorithm. Also, there is a limit in that the error may increase when communication with the ground station cannot be established for a long time. Recently, as the use of GNSS has become possible even in geostationary orbit satellites, real-time orbit determination using the navigation solution of the GNSS receiver has become possible. The conversion error generated in the ECEF to ECI coordinate transformation process, when using the navigation solution of the GNSS receiver, affects the orbit determination error. In addition, there may be cases where the use of GNSS is temporarily difficult in geostationary orbit. Considering these points, in this paper extended Kalman filter based orbit determination algorithm that use the navigation solution of the GNSS receiver. To minimize the orbit transformation error, the post-processed orbit navigation solutions calculated using Earth Orientation Parameters are used as measurement values. The simulation results show that the orbital determination error is finally reduced by applying the precise coordinate transformation, and stable orbit determination is possible even when the use of GNSS is temporarily difficult by applying the proposed algorithm.