Control capability evaluation based reconfigurable flight control for aircraft with failures

This paper focuses on the reconfigurable flight control problem of aircraft with control effectors failures and damages. The architecture of the reconfigurable control system based on control capability evaluating and reference model adapting is presented firstly. And the baseline control law is designed by the dynamic inversion method. Based on the concept of attainable moments, the control capability function under failures is defined. The control capability evaluating results are used to modify the reference model by fuzzy reasoning when the performance of aircraft is undergoing a severe degradation. The key aspects of the proposed system are tested in a 6-DOF nonlinear aircraft model. The simulation results show that the control capability evaluation based reconfigurable flight control system can improve the control performance and enhance the flight safety of the aircraft with failures and damages of control effectors.