Limit cycle oscillation control of wing with static output feedback control method

This paper presents a static output feedback controller (SOFC) for aeroelastic control of a cantilevered rectangular wing in low subsonic flow. For this purpose, an optimal formulation of this control method is developed, and a solution method is proposed for the related matrix equation. This optimal solution is obtained by solving combined Lyapunov and Riccati equations. At first these equations are transformed into a set of nonlinear algebraic equations and then are solved with iterative Newton–Raphson?s method. This solution method is applicable to the full state feedback case. The controller is designed to extend flutter boundary and suppress limit cycle oscillation (LCO) of a low aspect ratio rectangular nonlinear structural wing. This structural nonlinearity is given by Von Karman plate theory. Both full and reduced order aerodynamic models are examined based on the modified vortex lattice theory. Results show combination of SOFC with reduced order aerodynamic model would be an effective choice for aeroelastic stabilization, and this controller has a very comparable result with linear quadratic regulator (LQR).