Pitch angle control for hovering tilt rotor aircraft on one side rotor lift variation

In CACS2016 authors have proposed a roll angle control system for hovering tilt rotor aircraft (TRA) on one side rotor lift variation, which seriously affects the stability of TRA motion. And in this study as the next step a pitch angle control system of hovering TRA on the same situation is proposed under the assumption that the lateral-directional motion is already stabilized. Basically this flight control system consists of pitch rate feedback as stability augmentation method and P control as controllability augmentation method.