The high angle of attack aerodynamic modeling and nonlinear dynamic inversion flight control law design

摘要

A nonlinear dynamic inversion high angle of attack flight control method is approved in this paper. In order to validate the nonlinear controller performance, a 6-DOF aircraft model is built with nonlinear character, unsteady hysteresis character, asymmetry force and asymmetry moment character, wing rock character and so on. Based on the nonlinear dynamic inversion and singularly perturbed theory, the nonlinear high angle of attack flight control law is divided into two control loops: fast loop and slow loop. For each loop, nonlinear dynamic inversion method is used to design the control law and the calculated moment command is translated into four control surface commands. The high angle of attack maneuver simulation results show that the controller has excellent control performance.