Structural Damping Effect on Deformation of Flexible Flapping Wing

Flapping MAV is a recent area of extensive study because of its unique advantages including high maneuverability and information gathering capabilities. Numerous researchers have taken serious efforts in understanding and investigating the aerodynamics, flapping mechanisms and control implications. Moreover, the large flexibility of the wings leads to the study of complex fluid-structure interactions. Generally, most research has been dedicated towards the structural elasticity and natural frequencies rather than the effect of structural damping on the deformation of flapping wing. In this paper, finite element simulations of a flapping wing are tuned via static characterization and modal testing and compared with the DIC (digital image correlation) results. The amplitude of structural damping factors is evaluated and validated through simulation results and experimental results.