The air data assisted SINS/GPS/CNS fault-tolerant integrated navigation system design is proposed in this paper. The scheme combines the information of ADS system with SINS/GPS unit by Kalman filter, and takes advantage of the redundancy of ADS information to offset isolated GPS for fault detection. Improved federal filter is applied to data fusion for achieving optimal estimation of the aircraft. Simulation results demonstrate that the designed fault-tolerant federal filter algorithm can effectively maintain system accuracy and fault tolerance when GPS output is discontinued.
Research on SINS/GPS/CNS fault-tolerant integrated navigation system with air data system assistance
01.08.2016
355311 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2013
|Fault tolerant inertial navigation system
AIAA | 1988
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