Structural Deformation Measurements of Anisotropic Flexible Flapping Wings for Micro Air Vehicles

摘要: Anisotropic structural properties of flapping micro air vehicle wings have recently started to attract research attention. A difference in spanwise and chordwise stiffness, for various bending twisting behaviors during flapping, seems be the key factor producing lift thrust. This work presents an experimental setup post processing techniques characterize behavior response membrane with different topologies features. These tested represent typical designs used hobby ornithopters, are effective thrust generation forward flight. Wing deformation measurements interest current work. The rapid motions, large out-of-plane wing displacements, localized flexible membrane, small scale loads all challenge traditional measurement techniques. customized digital image correlation system, combined stroboscopic triggering fine-tuned acquisition, is developed determine kinematics surface both static vacuum environments. Results given along a as function frequency, vacuum/air conditions, anisotropic structure.