Abstract:

Flight stability and the flight control are the crucial for keeping an aircraft desired attitude and involving ability to change attitude. In the literature, many methods have been proposed to compare different flight stability and control performances. Increasing the maneuverability and ensuring the flight stability necessitate dealing with many nonlinear systems. In this study, aircraft roll control has been achieved by using LQR control technique. LQR method which is powerful and well known technique has been used for different control systems. The aircraft roll controller has been developed for ensuring fixed roll angle. While the aircraft is rolling slide slip angle is desired to keep zero. Pitch moment, roll moment and yaw moment are calculated and controlled in order to make the aircraft achieve a stable and reliable flight. The aircraft state-space model has been derived by using longitudinal and lateral equation of motion. An evolutionary optimization algorithm has been used to tune LQR parameters. LQR controller has been compared with PID controller. After determination of controller parameters; delay time, settling time, rise time, maximum overshoot and peak time has been measured for performance criteria.

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