摘要

An autonomous navigation method for low-thrust interplanetary vehicle is proposed. In the proposed navigation system, one inertial navigation system (INS) is employed to continuously estimate the position and attitude of vehicle, and three X-ray sensors observing X-ray pulsars are utilized to reduce the long-term effects of the errors in the INS. In addition, a modified square-root unscented Kalman filter (MSUKF) is proposed. The MSUKF adopts a fading factor to compensate the impact of modeling error, and contains no linearization steps. The results have shown that the proposed navigation system outperforms the traditional celestial-inertial method and the MSUKF could guarantee a faster convergence compared with former proposed nonlinear filters.