Autonomous orbit determination study for space navigation satellite

In order to improve the ephemeris accuracy of space navigation satellite,an autonomous orbit determination method is proposed.This paper not only builds the bidirectional pseudo-range measurement model,but also designs the two-step Kalman filter method.The satellite position and covariance are obtained in the first step by single point positioning method,which is considered as the pseudo-range measurement in second step to update orbital and time parameters.Moreover,the orbit orientation parameters are used to constraint the constellation rotation,solving the problem of rank deficiency of autonomous orbit determination.The simulation and analysis results illustrate the feasibility the proposed algorithm.