Roll angle control using opposite side rotor hub moment for hovering tilt rotor aircraft on one side rotor lift variation

In this study a synthesis of flight control system which is able to control the roll angle of hovering Tilt Rotor Aircraft (TRA) using the opposite side rotor hub moment on one side lift variation, which seriously affects the stability of hovering TRA motion, is proposed. Basically this flight control system is constructed with roll rate feedback as stability augmentation method and P or PI control as controllability augmentation method.