A hybrid NDI control method for the high-alpha super-maneuver flight control

This paper proposes a hybrid Nonlinear Dynamic Inversion (NDI) control method for the high angle of attack super-maneuverable flight control. In the post-stall flight regime, the problems of nonlinearity, time varying, coupling and uncertainties would arise, which is a big challenge for the flight control method. A hybrid NDI control method based on the angular acceleration feedback control is proposed to increase system robustness and performance. It is inspired by the idea of the NDI and the Increment NDI (INDI) control methods, and contains three parts: feedforward control, proportional control, and logical integral control. The hybrid NDI control method can not only increase system robustness, but also improve the system dynamic performance. To demonstrate the effectiveness of the method in the post-stall flight control, numerical simulations are conducted to evaluate its ability to handle system uncertainties, time-varying problems, and nonlinear factors. Simulation results show that the system responses are almost not affected by these complex, troublesome factors and have good performance and robustness.