复合材料仿生扑翼各铺层的有限元分析

Finite Element Analysis on Each Ply of Composites Materials Flapping Wing Aerial Vehicle

利用有限元法,对具有粘弹性的碳纤维复合材料设置一组铺层角度,以探究扑翼在空气动力和惯性力作用下的结构力学性能表现。在单层板的4个铺设角度(0°,90°,45°和-45°)中,-45°铺层角度可得到最小的等效应力,但对应的最大变形相对最大,45°铺层角度可得到相对最小的变形,但对应的等效应力较大,最大应力和最大变形不能统一在同一铺层角度的单层板仿生翼上。在层合板的铺层角度组合中(-45°/0°、-45°/45°、-45°/90°、0°/45°、0°/90°、45°/90°),45°/90°铺层组合可得到最小的等效应力和最小的结构变形,整体及各分层的最大正应力和剪应力区域产生于前缘梁根部,集中应力分布合理,具有较好的力学性能。最大应力和最大变形可以统一在双层层合板仿生翼上,具有比单层板更优的力学性能,这与昆虫翼的由腹、背两层高承力薄膜构成的翅膜微结构相似。本研究有助于解释昆虫翼的完美结构表现,并为扑翼设计提供借鉴。

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°,45°and-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 tomicro 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.