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本文采用大变形有限元方法进行纤维缠绕固体火箭发动机壳体的应力及爆破分析。采用最大应力强度准则进行单元失效判断，并引入合理的刚度衰退模型，从而较真实地模拟壳体的承载过程。在此基础上，重点讨论了材料性能、几休非线性对固体火箭发动机壳体封头部位相对承载能力的影响，特别是针对两个实际结构得出相反的影响结果，对结构的优化设计和实际应用的补强研究有指导意义。另外，从爆破的角度探讨了由模拟壳体外推真实固体火箭发动机壳体结构的合理性。
In this paper, the finite element method of large deformation of the fiber wound solid rocket motor shell stress and blasting analysis. The unit failure criterion is determined by using the maximum stress intensity criterion, and a reasonable stiffness decay model is introduced to simulate the bearing process of the shell more faithfully. On this basis, we mainly discuss the influence of material properties and several non-linearities on the relative bearing capacity of the head of solid rocket motor. Especially for the two actual structures, the opposite effects are obtained. The optimal design of the structure And practical application of reinforcement research has guiding significance. In addition, the rationality of shell structure of real solid rocket motor extrapolated from simulated shell was discussed from the perspective of blasting.