Design of Missile Attitude Controller Based on Nonlinear Dynamic Inverse Theory

摘要

The missile has the characteristics of multi-input and multi-output, strong nonlinearity and strong coupling in the course of flight, and also has the characteristics of complex aerodynamic effect and violent attitude change. Therefore, the traditional control method can't meet the requirements. Based on the nonlinear dynamic inverse theory, this paper divides the control system into fast loop and slow loop by using the idea of cascade structure control according to the characteristics of time scale difference in the dynamic response of state variables. The slow loop attitude controller and the fast loop attitude controller are designed by state feedback, which solves the problem of multi - input multi - output, strong nonlinearity and strong coupling of missile. Finally, the stability of the designed controller is verified by Lyapunov stability analysis. Based on the problem of large tracking error, a PI controller is designed on the basis of dynamic inverse controller to improve the accuracy of the controller. At the same time, the simulation results show that the controller has a certain perturbation of the aerodynamic parameters robustness.