关于无人机机翼复合材料结构模拟及有限元分析

On the Simulation of UAV Composite Structure and It's Analysis by FEM

基于半梁式全金属无人机机翼模型,用等刚度设计方法建立半复材、全复材的无人机机翼复合材料结构有限元模型。分析半复材、全复材机翼相对全金属机翼的减重情况,并对比三角形与四边形壳单元在不同网格密度下的有限元模型的计算结果,得出:(1)半梁式机翼可以更好发挥蒙皮承载作用;(2)等刚度法设计的全复材机翼减重将近50%;(3)有限元计算的收敛可以用最大位移判断,本机翼计算节点数达1 974时收敛。

By using a simulation model of UAV wing as half-beam type of all-metal and Equivalent Stiffness Design method,a model of UAV wing as half-composite and full-composite are established.Both the triangular shell element and the quadrilateral shell element with different mesh density are adopted for analysis of FEM.The weights of the models of half-composite and full-composite wing are used to compare with the all-metal wing.Calculating results show that:(1) Half-beam wing skin has a higher load-bearing capacity;(2) The full composite wing is nearly 50% weight loss from all-metal wing;(3) The maximum displacement can be used to evaluate the convergence of FEM,for instance when the number of node is 1 974 of the present model the requirement of convergence can be satisfied.