Control System Design for Small Unmanned Aerial Vehicle

The first component includes development of a physical inertial and aerodynamic model representing an existing UAV in research. Second is the development and implementation of six degrees of freedom simulation employing the developed model. The third component is the comparison between open loop flight and the UAV dynamics with the MATLAB simulation results. The simulation results show that the responses of the altitude control for small UAV are oscillated because of the wind disturbances in level flight condition. To apply the UAV system the feedback control design is of linear quadratic regulator (LQR) and proportional integral derivative (PID) architectures.