Abstract:
The ability of UAV to do a certain task is mainly dependent on accuracy of its control system. The purpose of this project is to analyze and design pitch control system for the UAV model in short mode, Too long settling time is noted after the model whose aerodynamic data are available have been analyzed by Using Simulink. The main objective of this research is to Suggest and design one of the suitable controllers to Control the model. The result obtained when applying PID controller is not satisfactory. Good result is obtained by using state feedback controller to control pitch. And the system has been stable upon the step input.
