Research on adaptive nonlinear dynamic inversion fault-tolerant flight control system based on sideslip trim strategy

Purpose Loss of control and air crashes are frequently caused by aircraft faults. Therefore, a practical control strategy can prevent aircrafts from losing control without control laws reconstruction. The purpose of this paper is to propose a sideslip trim fault-tolerant control strategy for wing damage and aileron stuck. Design/methodology/approach The six degree of freedom model of the damaged aircraft is constructed by using the non-center-of-mass approach on the basis of aerodynamic database, which is calculated in XFlow. This paper adopts the sideslip command for trim, combining with the adaptive nonlinear dynamic inversion control to achieve fault-tolerant control. Findings This strategy can effectively improve the control margin of the remaining control surface and guarantee maneuverability of the aircraft after serious faults. Originality/value The original and wing-damaged aircraft models are reconstructed in CATIA, and the aerodynamic data is calculated in XFlow. Sideslip angle is adopted to compensate additional roll moment caused by wing damage or aileron stuck. Adaptive nonlinear dynamic inversion control, combined with sideslip trim, is applied to achieve fault-tolerant control.