Vibration Suppression in Flight Control with Dynamic Inversion

Classical flight control design techniques treat the aircrafts as rigid bodies. Extra effort and time is required for the development of a separate vibration controller that addresses the flexible nature of the aircraft. Researchers have concentrated in developing integrated design techniques where a single controller is designed to provide satisfactory control of the rigid modes, and vibration suppression of the structural modes. This paper presents the application of such an integrated design procedure for the pitch rate control of a twin-fin combat aircraft. The proposed technique is easy to apply and generates a simple, low-order controller that satisfies the design objectives.