Flutter and Limit Cycle Oscillation Control of A Nonlinear Wing with ActuatorS Saturation

Flutter and limit cycle oscillations (LCO) control ofa structural non-linear wing with actuator saturation is considered in this paper. For this purpose composite nonlinear feedback (CNF) theory is used. The CNF theory accounts for the effect of actuator saturation and here it can be shown, this control method can effectively suppress the flutter and LCO of a structural nonlinear wing with constrained input. The aeroelastic model is a low aspect ratio rectangular wing in a low subsonic flow with structural nonlinearities. The structural nonlinearity arises from double bending in both chord-wise and span-wise directions (Von Karman plate theory). For aerodynamics modelling a full and reduced order aerodynamics model based on the modified vortex lattice method is used. Results from simulations show, with this simple controller, we can effectively suppress LCO and extendflutter boundary.