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.
An integrated navigation algorithm for Aerospace Vehicle based on extended H∞ filter
01.07.2014
457031 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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