Study on Completely Autonomous Integrated Navigation Technology for Space Maneuvering Vehicle

To satisfy the engineering requirement of completely autonomous navigation for space maneuvering vehicle, a method of SINS/CNS/GNS integrated navigation method is proposed. The state model is established based on the error equations of strapdown inertial navigation system(SINS), and the mixedly corrected Kalman filters composed of the subfilters of SINS/CNS and SINS/GNS are designed. Then the federal filter is used to obtain the optimal estimations of SINS/CNS/GNS parameters. Simulation results show that the proposed method significantly improve the navigation accuracy and the stability of filter, and has the value of engineering application.