LQG control of a CFD-based aeroelastic wing model

This paper presents a linear quadratic Gaussian (LQG) algorithm for suppression of flutter in an aeroelastic wing. CFD-based input output data and autoregressive moving average identification method were employed to develop a state space model for aerodynamic forces. A finite element model of the wing was constructed to obtain the flexible modes and a second set of linear state space equations representing the structural dynamics of the wing. The outputs of the coupled aeroelastic model, pitch, plunge, and the movement of the control surface at the trailing edge of the wing were used to design a combined state estimator and a linear quadratic regulator. Simulation results presented validates the effectiveness of the controller to suppress flutter induced by increasing dynamic pressure.