A technique was developed which provides reliable failure detection and identification (FDI) for a dual redundant subset of the flight control sensors onboard the NASA F-8 digital fly by wire (DFBW) aircraft. The technique was successfully applied to simulated sensor failures on the real time F-8 digital simulator and to sensor failures injected on telemetry data from a test flight of the F-8 DFBW aircraft. For failure identification the technique utilized the analytic redundancy which exists as functional and kinematic relationships among the various quantities being measured by the different control sensor types. The technique can be used not only in a dual redundant sensor system, but also in a more highly redundant system after FDI by conventional voting techniques reduced to two the number of unfailed sensors of a particular type. In addition the technique can be easily extended to the case in which only one sensor of a particular type is available.


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    Title :

    Reliable dual-redundant sensor failure detection and identification for the NASA F-8 DFBW aircraft


    Contributors:

    Publication date :

    1978-02-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Dual redundant sensor FDI techniques applied to the NASA F8C DFBW aircraft

    Desai, M. N. / Deckert, J. C. / Deyst, J. J. et al. | NTRS | 1976




    F-8 DFBW sensor failure identification using analytic redundancy

    Deckert, J. C. / Desai, M. N. / Deyst, J. J. et al. | NTRS | 1977


    A reliable dual-redundant sensor FDI system for the NASA-DFBW aircraft

    Deckert, J.C. / Desai, M.N. / Deyst, J.J. | Tema Archive | 1976