Abstract: A structure analysis was conducted in this study on membrane flapping-wing aerial vehicles using finite element method based on composite material models in order to study the mechanical performance of flapping wing under aerodynamic and inertial forces. The results show that among the four orientation angles (0°, 90°, 45ånd -45°) of composite fiber on the single layer plate, using -45° can get the least stress and the largest deformation, using 45° can get the least deformation and the relatively large stress, the maximum stress and the maximum deformation could not be unified on the single layer plate at the same ply angle. Among the orientation angle combinations of composite fiber(-45°/0°、-45°/45°、-45°/90°、0°/45°、0°/90°、45°/90°) on the double-layer plate, using 45°/90° can get the least stress and least deformation. The maximum normal stress and shear stress zone of the whole and each layer are generated at the root of the beam. The stress distribution is reasonable and the mechanical property is better. The maximum stress and deformation can be unified in double laminated bionic wing, it means the double-layer plate which is similar to micro structure of insect wing has better mechanical properties than the single layer plate. This research is helpful in answering why insect wings are so impeccable, thus providing a possibility of improving the design of flapping-wing aerial vehicles.