Robust aeroelastic control of two-dimensional supersonic flapped wing systems

The performance of a robust control strategy applied to a two-dimensional supersonic flap-wing aeroelastic system impacted by a pressure pulse in the subcritical supersonic flight speed regime is analyzed. The piston theory aerodynamic model modified to account for the flap deflection has been considered. The study is carried-out via implementation of the Linear Quadratic Gaussian (LQG) control methodology with sliding mode observer. Its performance toward suppressing flutter, reducing the vibrational level amplitudes, as well as toward eliminating the observation spillover due to the unmeasured states is revealed through numerical simulations, and pertinent conclusions are outlined.