纤维缠绕固体火箭发动机壳体爆破问题研究  

THE BURSTING STUDY OF FILAMENT WOUND ROCKET MOTOR CASE

作　　者：孙雪坤[1] 郭燕阳[2] 杜善义[2] 

机构地区：[1]东北大学轧制技术及连轧自动化国家重点实验室 [2]哈尔滨工业大学复合材料研究所

出　　处：《宇航学报》1998年第4期90-94,共5页Journal of Astronautics

摘　　要：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 we employed the nonlinear finite element method to calculate the stress and bursting pressure of filament wound rocket motor case.The Maximum stress criteria and the stiffness degradation were introduced to the failure analysis.Therefore we can simulate the working precess of the case.Especially the effects of the material performance and nonlinearity on the loading capacity of the dome were also discussed.Diverse results were gotted for two different cases and they can be used to guide the optimum design and mending strength of the case.Otherwise,from the view point of burst,the way from simulated case to real structure was also discussed.

关 键 词：固体火箭发动机 壳体 有限元 爆破 纤维缠绕 

分 类 号：V435.22[航空宇航科学与技术—航空宇航推进理论与工程]