A Study on Spin Turn Mode for Hovering Tilt Rotor Aircraft

In this study a synthesis of Control Configured Vehicle (CCV) flight control system which is able to realize the spin turn for hovering Tilt Rotor Aircraft (TRA), using the forward/backward alternative same angle variations of lift vectors of both rotors, is proposed. Basically this flight control system is constructed with roll angle feedback as stability augmentation method and P and PI control as controllability augmentation method.