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合理的传力路径是保证固体火箭发动机喷管设计成功的关键因素。本文针对某型号复合喷管,建立了流固域一体化的数值计算模型;采用燃气流动/固体导热强耦合与结构应力弱耦合的流/固/热耦合分析方法,结合热试车试验现象,基于有限元分析技术,着重研究了轴向传力路径以及应力场特征。数值计算结果表明:复合喷管轴向传力路径太过曲折,导致双层结构型式的扩张段呈现出严重的局部承载特征,并且调整间隙配合量不能从根本上缓解扩张段内外壳间限位凹槽处的挤压程度。在传力路径和热结构分析基础上,总结出热试车试验现象的成因,给出了结构设计改型的建议,可供设计单位参考。
Reasonable force transmission path is to ensure the success of solid rocket engine nozzle design key factors. In this paper, a numerical model for the integration of fluid-solid zone is established for a certain type of composite nozzle. The flow / solid / thermal coupling analysis method of strong coupling of gas flow / solid thermal conductivity and structural stress is adopted. Combined with the phenomenon of thermal test, Finite element analysis technology, focusing on the axial force transmission path and stress field characteristics. The numerical results show that the axial force transmission path of the composite nozzle is too tortuous, resulting in serious local load-bearing characteristics in the dilatation section of the double-deck structure. Adjusting the amount of the gap can not fundamentally alleviate the limit between the inner and outer shells The degree of squeezing at the groove. Based on the analysis of the transmission force path and the thermal structure, the causes of the phenomenon of hot test run are summarized, and the suggestions of the structural design modification are given, which can be used by the design unit for reference.