An integrated navigation algorithm for Aerospace Vehicle based on extended H∞ filter

To reduce the effect of changes in gravity field and radius on Aerospace Vehicles navigation system, an inertial navigation algorithm in launch inertial coordinate for ASV is studied in this paper firstly. To overcome the poor performance of Kalman filter in uncertain environment, an extended H_∞ filtering algorithm is designed secondly. Combining the advantages of launch inertial coordinate and H_∞ filter, an integrated navigation algorithm for Aerospace Vehicle is proposed in this paper. The simulation results show that the proposed algorithm can improve the accuracy of the navigation system for ASVs.