飞机结构整体优化和细节分析

飞机结构复杂，部件众多，连接形式复杂，传统的单一计算方法已很难满足计算要求，为更好地挖掘飞机的承载能力，还要考虑结构局部进入塑性区应力分布.对飞机结构进行有限元分析，有时需同时考虑整体和局部，大型结构采用较密的网格会耗费大量时间、资源等，甚至会导致计算不收敛；局部结构须划分较细的网格才能得到局部构件的细节应力.以某型飞机机翼为例，简单介绍开展飞机结构整体优化和细节分析的方法与流程.

Overall optimization and detail analysis of aircraft structure

The traditional single calculation method is difficult to meet the calculation requirements of aircraft structures, which involves different kinds of components and join methods. Sometimes, in order to improve carrying capacity of the joint structures, the plastic stress distribution is even considered for the local areas of structure. The detail analysis is often considered in the whole analysis during the finite element analysis. Regarding the large scale structure, it costs the massive time and resources in the calculation using dense mesh, which even causes that the calculation does not converge. The thin mesh must be used to regard the partial structure which could obtain the partial component's detail stress. The calculation on an airplane wing is taken as an example to demonstrate the methods and processes of the overall optimization and detailed analysis of aircraft structures.