Sliding mode variable structure control of flutter suppression for two-dimensional wing

Active flutter suppression (AFS), an attractive branch of aeroelasticity, and playing an important role of aircraft design was conducted on a two-dimensional wing which had a tailing-edge control surface. Sliding mode control (SMC) for AFS and its feasibility were investigated theoretically. The basic equations of motion were established by using quasi-steady aerodynamics forces. A sliding mode surface and a state feedback control for switching were designed in state space to achieve AFS. The principle of system stability provided by the SMC was discussed by state variables trajectory analysis. Further discussions about system robustness and time delay effects were also given. The results indicate that SMC strategy could be used for AFS and has potential usefulness in active aeroelastic control.