Active Flutter Suppression of a Two-Dimensional Airfoil with Actuator Saturation

Abstract

This paper presents a systematic methodology to evaluate the feasibility of suppressing airplane flutter instabilities through the actively controlled closed-loop actuation of control surfaces in presence of actuator deflection constraints. When active flutter suppression proves to be feasible, the methodology synthesizes a preliminary feedback law able to augment flutter stability of the aeroelastic model under investigation. If active flutter suppression proves to be not viable due to the physical limitations imposed by actuator deflection saturation, the methodology can be employed in a parametric manner to define the actuator performance requirements that would take to implement active flutter suppression. The theoretical background of the methodology is presented and its implementation is validated employing the generic twodimensional wing section of Theodorsen.