In this paper, an approach to detect and isolate the aircraft sensor/control surface faults affecting the mean of the Kalman filter innovation sequence is proposed, and a new structure for a fault tolerant aircraft control system is presented. In the simulations, the longitudinal and lateral dynamics of an F-16 aircraft model is considered, and detection and isolation of pitch rate gyro faults and control surface faults are examined. The principal block diagram of a fault tolerant aircraft control system is illustrated.


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    Title :

    Sensor/Control Surface Fault Diagnosis and Reconfiguration in Aircraft Control Systems


    Contributors:
    Hajiyev, Ch. (author) / Caliskan, F. (author)

    Conference:

    Ninth Biennial Conference on Engineering, Construction, and Operations in Challenging Environments ; 2004 ; League City, Houston, Texas, United States



    Publication date :

    2004-03-03




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




    Sensor/Control Surface Fault Diagnosis and Reconfiguration in Aircraft Control Systems

    Hajiyev, C. / Caliskan, F. / American Society of Civil Engineers | British Library Conference Proceedings | 2004



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