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).