Vibration control design for a flapping wing of micro aerial vehicle

The vibration regulation problem is addressed for a flexible wing of the micro aerial vehicle (MAV) in this article. The flapping wing is considered with the flexible feature. We model the flapping wing as a DPS (distributed parameter system). Thus, we use the PDEs (partial differential equations) to describe the wing bending and the wing twist. Boundary control force and twisting moment are proposed to regulate the bending deflection and the twist deflection of the flapping wing. The proper Lyapunov function is chosen to prove the stability. Lastly, we use the numerical simulations to verify the control performance.