Modeling and Control of a Fixed-Wing High-Speed UAV

Abstract

Due to their inventiveness in achieving high speeds while maintaining excellent agility, high-speed UAVs will be an interesting field of study in today's aviation technology. In this study, modeling and control of a fixed-wing high-speed UAV are performed. Geometric design and aerodynamic analysis are executed of the UAV with the help of some CFD software. Flight performance after a doublet control surface disturbance is evaluated with 6DOF flight simulations in both longitudinal and lateral directions by a developed MATLAB/Simulink code. Two kinds of different linear controllers, which are PID and LQR-I, are designed to hold the pitch angle of the UAV in the desired value. The time responses of the controllers are represented, and the elevator deflection effort is evaluated. Finally, a compulsive pitch angle is wanted to be tracked by the two controllers, and their responses are compared in terms of performance and stability.