本文提出一个适合于飞机结构非线性分析的有限元素组合算法。考虑到元素材料屈服和/或失稳后出现的非线性问题导出了有限元计算格式。本方法已经实际用于描述××型直升机结构静力试验从开始加载到局部损伤或失稳、扩展直至破坏的全过程受力状态;用于确定该机结构的最大承载能力和破坏部位,并取得了非常好的结果。文中介绍了数值算例及其与试验结果的对此。 This paper presents a finite element combination algorithm suitable for non-linear analysis of aircraft structures. The finite element calculation format was derived considering the non-linearity of the element material after yielding and / or buckling. This method has been actually used to describe the full load capacity of X-type helicopter structure static test from the beginning of loading to local damage or instability, extending to the destruction of the whole state of force; to determine the maximum load carrying capacity of the aircraft structure and damage sites, and Achieved very good results. In this paper, numerical examples and their results with the experimental results are presented.