Design of flight control system for an aeroelastic aircraft

Abstract

The evolution of modern day aircraft increases the interaction between aeroelastic dynamics and control laws, known as aeroservoelasticity. An integrated flight control system without structural filters is proposed in order to achieve good handling qualities and increase structural mode damping. In the first step sensor and actuator location is studied, and in a second step the use of the linear quadratic regulator with output feedback for the synthesis of the control law.<>