Uav Flight Control System Simulation

The primary purpose of this thesis is to apply classic PID control and intelligent PID control strategies to the design of the UAV's(Unmanned Aerial Vehicle)fight control law. First of all, the UAV's six-degrees-of-freedom(6-DOF) mathematical model is built and linearized. Then some basic theories and techniques about classic PID control and intelligent PID control are mentioned followed by a profound research on the control scheme of the lognitudinal and lateral control system of the UAV. Classic PID and intelligent PID control strategies are respectively applied to the design of the flight control law of the UAV's four fundamental flight control mode, including pitching angle control mode, altitude holding mode, rolling angle control mode and yaw angle control mode. Finally, an amount of simulation is designed to validate the effectiveness of the flight control law based on classic PID and intelligent PID control strategies. The results of the simulation show that the classic PID flight control law is effective, and the intelligent PID flight control law is superior to the former one.