Autonomous orbit determination method for navigation satellite during orbit maneuver based on accelerometer

In order to reduce the dependence of the ground station, it is of great importance to improve the autonomous operation ability of the navigation satellite. During the orbit maneuver, the autonomous orbit determination error of the navigation satellite will be enlarged. In order to resume the precise ephemeris of the navigation satellite quickly, which can enhance the application efficiency of the navigation satellite system, a new autonomous orbit determination method for the navigation satellite is presented. The proposed method is an improvement of the traditional celestial navigation method, in which the accelerometers are used. The acceleration value will be added to the orbit dynamics function. Meanwhile, the estimation error square matrix of the ex-tended Kalman filter will be reset during the orbit maneuver phase. Simulation results show that the convergence time and estimation error will be reduced effectively by the proposed method.