Fault-Tolerant Control of Wing Surface Based on Incremental Nonlinear Dynamic Inversion

The damage to the aircraft wing not only disrupts the aircraft’s inherent structure but also alters its aerodynamic characteristics, posing a serious threat to the safety of aircraft flight. In case of wing damage, pilots can save the aircraft by making sound decisions and using proper manipulation techniques if the flight control system is still operational, preventing catastrophic accidents. This paper takes a large transport aircraft as the research object and delves into the key issues involved in the fault-tolerant control method of the flight control system’s wing sur-face. A fault-tolerant control method with control allocation based on incremental nonlinear dynamic inversion is proposed. This method performs control allocation according to fault information and utilizes control surface deflection to estimate the angular acceleration signal, significantly enhancing the aircraft’s robustness against wing surface faults. Simulation results demonstrate that the designed fault-tolerant flight control law can ensure the normal flight of the aircraft in the event of a single wing surface failure.