基于PATRAN/NASTRAN的复合材料机翼蒙皮优化设计

基于有限元分析软件PATRAN/NA STRAN建立了适用于大型复合材料结构的优化系统。对层压板的优化分2级交替进行:第1级优化采用最大应变能准则调整各分层比例;第2级优化先用射线步调参,再从K uhn-Tucker条件和满应力准则出发推导出满足位移约束和强度约束的单元厚度迭代因子进行单元厚度优化。针对文中的优化方法,以复合材料机翼盒段蒙皮铺层优化为例进行了数值计算,通过优化计算验证了该方法有较高的效率,对工程设计具有一定的应用价值。

Efficiently Optimizing Skin of Composite Wing Structure with PATRAN/NASTRAN

Purpose.There exist several papers~() on optimizing layer design of skin of composite wing structure;but,in our opinion,they are very inconvenient as a practicable design method.We now propose an efficient design method that is easily practicable.In the full paper,we explain in detail the proposed efficient method;in this abstract we just list the two topics of our explanation:(A) the method for optimizing layer design;mathematically it includes eqs.(1) through(13) in the full paper;(B) flow chart of optimization process;PATRAN is used for establishing finite element model of wing structure needed in layer design;Fig.1 in the full paper shows the flow chart that contains explanations on how the various steps of design are performed by using the powerful NASTRAN. As an example,a composite wing box structure is analyzed and optimized.The results,as graphically shown in Fig.3 in the full paper and numerically given in Table 1,show preliminarily that our proposed method has good efficiency and convergent speed.