Based On Dynamic Inversion Flight Control System Design And Simulation

The thesis is divided into two parts. In part Ⅰ , we mainly study the design of nonlinear control laws of aircraft with thrust vector based on Dynamic Inversion method. Dynamic Inversion method can be used to solve the problems of super-maneuvers and unconventional maneuvers. In this part, nine state variables are adopted and divided into 3 categories: the fast variables, the medium-slow variables and slow variables. Fast variables are angular velocities. Medium-slow variables are angular parameters of aircraft. Slow variables are trajectory parameters. These variables are designed into three-level serial subsystems. By studying each subsystem carefully we get a set of dynamic inversion algorithm of nonlinear control problem for each subsystem, at the same time, taking into other factors, such as fusion of thrust vector and pneumatic surface of rudder, the dynamic inversion controller is designed.In the part Ⅱ, the application of dynamic inversion method in the direct lift control task is studied. Direct lift can increase aircraft's rapidity, sensitivity, accuracy in trajectory control task. Based on its basic conception and rationale, we discuss the direct lift in detail. According to the characters of Dynamic Inversion method in making multivariable control system decoupling, we design a set of control law for every direct lift control mode.