Real-Time Kinematic Orbit Determination of GEO Satellite with the Onboard GNSS Receiver

The spacecraft has widely used Global Navigation Satellite System (GNSS) in precise navigation, attitude determination, formation flight and time synchronization. For high earth orbit spacecraft, the space environment is very challenging for GNSS receivers to work. Taking the No. 2 Telecommunication Technology Test satellite (TTS-2) as an example, under both preprocessing strategies of the carrier phase smoothing pseudorange algorithm and single receiver fault detection algorithm based on residual, this paper analyzes the real-time kinematic orbit determination capability of Geostationary Earth Orbit (GEO) satellite by standard point positioning (SPP) and kinematic precise positioning (KPP). The experimental results show that the 3D error of the SPP kinematic orbit is about 100 m, and that of the KPP kinematic orbit is about 20 m. Carrier phase smoothing pseudorange and single receiver fault detection algorithm based on residual are used to preprocess the onboard GPS data, they reduce the 3D error of the SPP kinematic orbit to 49.4 m and radial error to 46.4 m, which decreased by 45%. And they reduce the 3D error of the KPP kinematic orbit to 16 m, a reduction of 23%, and the radial error to 10 m, a reduction of 34%. The kinematic orbit is convenient to implement the hardware and software of the onboard GNSS receiver, and the real-time and high-precision position provides favorable conditions for the accurate orbit control of the spacecraft. This paper’s research work and conclusion have important reference value and significance for the application of high-orbit GNSS, and will promote the development of space-borne GNSS application.