Dynamic Inversion-Based Flight Control for Supersonic Civil Aircraft with High Angle of Attack

Aiming at the problem of severe nonlinearity of supersonic civil aircraft maneuvering with high angle of attack (AOA), a flight control method based on the dynamic inversion (DI) is proposed in this paper. According to the time-scale separation principle, the supersonic civil aircraft control system is divided into attitude subsystem and altitude subsystem to design dynamic inversion controllers, respectively. Thereinto, the attitude subsystem is divided into internal and external loops according to different state quantities of response speed. The internal loop is used to track the pitch angle speed and the external loop is used to track the angle of attack instruction. The altitude subsystem is used for speed control. The simulation results of the proposed method show that the designed dynamic inversion vertical controller has a good tracking effect, and can quickly track the angle of attack command and the speed command. This method can effectively alleviate the nonlinear maneuverability and stability of supersonic civil aircraft flying at the high angle of attack.