整体成型复合材料模型机翼设计方案优选与验证

采用多级优化方法，对给定外形和尺寸的复合材料模型机翼进行了设计方案优选。首先基于单因素的效能评估和灰关联度的综合效能评估对机翼进行了结构布局设计，然后采用有限元法对工字梁机翼进行结构细节优化与铺层设计，最后采用基于真空袋法的整体成型工艺制备了蒙皮-夹芯、蒙皮-加筋、C型梁和工字梁等4种典型结构的复合材料模型机翼，并利用三点弯曲试验对优选设计方案进行了验证。优化结果表明：工字梁机翼结构效能水平最高，其次是后C型梁机翼，结构效能最差的是蒙皮-腹板机翼，梁凸缘采用等厚度变宽度可获得近似等强度梁结构。试验结果验证了优化设计方案的有效性。

Optimization design and testing of composite wing model via integral forming process

According to the given configuration and dimension of composite wing model, the multilevel optimization method was used to determine the design scheme of wing. First, the efficiency evaluation of single factor and comprehensive efficiency evaluation of grey correlation degree were introduced to obtain the optimum wing layout. Then, the structure detail optimization of I-beam wing based on the finite element method and ply design were carried out. Finally, four kinds of typical composite wing models (i.e. skin-foam structure, skin-stiffened structure, front C-beam structure and I-beam structure) were manufactured by using integral forming process based on the method of vacuum bag. Then the three point bending test was used to verify the optimization design. The optimization results show that the I-beam wing has the highest structural efficiency, then followed by the back C-beam wing. The skin-web wing performs with the least structural efficiency. The flange can gain approximate equal strength beam by using constant thickness and variable width. The effectiveness of the optimization method was verified by the experimental results.