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.


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    Title :

    Research on SINS/GPS/CNS fault-tolerant integrated navigation system with air data system assistance


    Contributors:
    Shengnan Li (author) / Jinsong Mei (author) / Qiang Qu (author) / Kai Sun (author)


    Publication date :

    2016-08-01


    Size :

    355311 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English






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