Adaptive Linear Quadratic Gaussian Optimal Control Modification for Flutter Suppression of Adaptive Wing

This paper presents an adaptive control approach for flutter suppression of a performance adaptive aeroelastic wing equipped with a variable camber continuous trailing edge flap design. The adaptive control approach is based on the optimal control modification method augmented to a linear quadratic gaussian optimal control design. A model reduction based on a singular perturbation approach is presented. The control surfaces are subject to relative motion constraints due to the elastomer transition material in between the flap sections. A virtual control method is proposed using a shape function to deal with the relative motion constraints. Simulation results indicate that the adaptive augmentation control design is effective in suppressing unstable aeroelastic modes.