Simulation Study on Real-Time Orbit Determination Based on GNSS for LEO Satellite Considering the Effect of Electric Propulsion

The traditional GNSS pseudo-range based Real-Time Orbit Determination(RTOD) cannot meet the requirements for high-precision and reliable orbit determination of LEO satellite with electric propulsion in the whole process, this paper conducts mathematical modeling of electric thrust based on the magnitude, direction and satellite attitude of electric thrust, improves the traditional GNSS pseudo-range based RTOD algorithm, and takes into account the impact of inertial system acceleration generated by electric thrust during the Kalman time update process of RTOD, A new RTOD algorithm based on GNSS pseudo-range considering the influence of electric propulsion is proposed. Then, based on GNSS signal simulator and space-borne GPS/BDS receiver, the simulation scenarios of single electric thruster and dual electric thruster are designed and simulation GPS/BDS data are collected. Using the independently developed RTOD software SATODS, offline simulation RTOD data processing tests are conducted on the collected simulation data. The test results show that the new RTOD algorithm based on GNSS pseudo-range considering the influence of electric propulsion proposed in this paper is not affected by the electric thrust, which verifies the adaptability of the improved RTOD algorithm to the orbit determination of orbital maneuver conditions with the electric propulsion.