机翼复合材料加筋壁板结构的优化设计

Optimization Design for Stiffened Composite Wing Panel

为了提高机翼复合材料加筋板结构的承载效率,把总体屈曲载荷、局部屈曲载荷和静载荷相等作为最优化设计准则,利用稳定性效率因子图和复合材料稳定性分析方法实现机翼复合材料加筋板结构的初步优化设计。利用编写的PCL二次开发程序进行参数化建模分析,可以较快地得出不同材料和载荷情况下的稳定性效率因子图。结果表明:通过稳定性效率因子图结合复合材料加筋板结构的稳定性分析方法,可以较快实现机翼加筋板结构的初步优化设计,所得结构具有相对较高的承载效率。

For loading efficiency of stiffened composite wing panel ,the equality of global bucking load ,local buc-king load and static load is used as the optimization design principle .Using the concept of stability efficiency fac-tor and composite material stability analysis method ,the primary optimal design of stiffened composite wing structures are realized .The efficiency factor diagram of different materials and load cases is obtained by PCL secondary development codes .Results show that the method by using the efficiency factor graph with composite material stability analysis method can rapidly realize the stiffened composite wing panel primary design with high load carrying efficiency .