基于改进跟踪微分器的增量动态逆控制器设计

Aiming at the strong aerodynamic nonlinearity and model uncertainty in high angle of attack flight control processes, an incremental dynamic inverse control method based on an improved tracking differentiator is proposed. Considering the dynamic characteristics of attitude control for aircraft at high angles of attack, a controller is designed with an outer loop for dynamic inversion and an inner loop for incremental dynamic inversion. Aiming at the problems of signal flutter and poor filtering effect when using traditional tracking differentiators to obtain the angular acceleration information required for incremental dynamic inversion, an improved tracking differentiator is designed by combining nonlinear and linear functions. Through high angle of attack flight numerical simulation, it is verified that the designed tracking differentiator has a certain degree of noise resistance while accurately extracting angular acceleration. The incremental dynamic inverse controller designed based on this differentiator enhances robustness to aerodynamic uncertainty.