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