An adaptive modified two-stage linear Kalman filtering algorithm is utilized to identify the loss of control effectiveness and the\nmagnitude of low degree of stuck faults in a closed-loop nonlinear B747 aircraft. Control effectiveness factors and stuck magnitudes\nare used to quantify faults entering control systems through actuators. Pseudorandomexcitation inputs are used to help distinguish\npartial loss and stuck faults. The partial loss and stuck faults in the stabilizer are isolated and identified successfully.
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