A new model-free method performing closed-loop fault diagnosis for an aeronautical system

International audienceFault diagnosis for a closed-loop controlled aeronautical system is considered. The geometry of the problem, the nonlinear model of the aircraft and two guidance laws are described. A new approach to perform fault detection, based on the study of the control signals, is then introduced. The method proposed allows the detection and isolation of actuator faults. Simulation results with measurement uncertainty illustrate the relevance of the approach. The influence of the guidance law and perspectives are discussed