复合材料机翼上蒙皮仿真分析与补强

Simulation Analysis and Reinforcement of Composite Airfoil Upper Skin

根据某无人机机翼的气动外形,采用壳单元模拟复合材料机翼上蒙皮,建立了该机翼的有限元模型,得到其在最严重工况下的有限元分析结果。以应变为判断标准,有限元分析结果表明,在靠近翼根处上蒙皮受力严重,应变过大。为减小上蒙皮应变,通过增加复合材料铺层的方法对上蒙皮进行补强,并对补强后的上蒙皮进行有限元分析,结果表明,补强后上蒙皮的应变降低,满足设计要求。

According to the aerodynamic shape of a UAV wing,the shell element is used to simulate the skin on the composite wing,and the finite element model of the wing is established.Using strain as the criterion,the result of the finite element analysis shows that the skin near the wing root is severely stressed and the strain is too large.In order to reduce the upper skin strain,the upper skin is strengthened by adding composite lamnation. The finite analysis result of the reinforced skin shows that the strain is reduced and meets the requirement of design.