Design of Aircraft Angle of Attack Control Law Based on Model-Free Adaptive Control

The longitudinal static stability of the aircraft during maneuvering is affected by the angle of attack. To enhance the stability, it is necessary to design an aircraft stabilization system. Aiming at the problem that the traditional model-based adaptive control method depends too much on the system model in the process of obtaining the control law, a data-driven full-form dynamic linearization-based model-free adaptive control method (FFDL-MFAC) is used to design the flight control law. The appropriate step size factor and the dimensions of the input and output data are selected according to the characteristics of the controlled system. The pseudo-partitioned gradient (PPG) is decoupled according to the structural characteristics of the control law. The decoupling vector contains the connection between inputs and outputs, which can obviously reduce the difficulty of calculation. The method of this paper is used to design the control law of F-16 aircraft longitudinal stabilization system and carry out simulation analysis. After analyzing the results of simulation, it can be shown that the control system based on FFDL-MFAC method has a more flexible structure and meets the requirements of longitudinal stabilization control.