Fault detection, isolation and accommodation in flight control system of A340-airbus aircraft

Abstract

Optimal linear Kalman filter (OLKF), fault detection, fault isolation, Robust Kalman filter (RKF) and reconfigurable Kalman filter algorithms have been applied on the control system of an Airbus-340 aircraft this study. The discrete flight dynamic model of the Airbus A-340 aircraft is presented and discussed. Sensor faults have been implemented in two scenarios: continuous bias fault and noise increment fault. The fault isolation proposed algorithm involves the computation of the statics which is a rate of sample and theoretical variances. The algorithms for fault-tolerant estimation of aircraft states are discussed. Two types of fault accommodation algorithms: RKF and reconfigurable Kalman filter are investigated. Two different approaches of RKF have been tested applied to the Airbus A-340 aircraft model of dynamics: single measurement noise scale factor (SMNSF) and multiple measurement noise scale factor (MMNSF).