高旋固体火箭发动机热固耦合特性数值分析  

Numerical Analysis of Thermal Solid Coupling Characteristics of High-spin Solid Rocket Motors

作　　者：武艳 夏瑛 林建民 袁泽建 WU Yan;XIA Ying;LIN Jianmin;YUAN Zejian(The Air Force’s Third Military Representative Office in Xi’an Region,Xi’an 710000,China;Northwest Industrial Group Co.,Ltd.,Xi’an 710000,China)

机构地区：[1]空装驻西安地区第三军事代表室,陕西西安710000 [2]西北工业集团有限公司,陕西西安710000

出　　处：《新技术新工艺》2025年第2期44-47,共4页New Technology & New Process

摘　　要：通过研究固体火箭发动机燃烧室金属壳体在高温高旋工作状态下的受力情况,为发动机设计时金属材料热强度提供依据,基于Fluent和ANSYS商业软件进行发动机热固耦合仿真分析,获得燃烧室在温度和工作压强耦合情况下温度场和结构受力变化。结果表明,当选用40Cr时,壳体正常工况下温度已超过400℃;结合材料的热拉伸试验分析,此时强度大幅下降,需提高安全系数。因此在设计时应综合考虑高温、高转速、高压力环境等因素,合理设计燃烧室壳体厚度。Through studying the stress of metal shell of solid rocket motors combustion chamber under high temperature and high spin,and thus providing a basis for the thermal strength of metal materials in the design of the engine,it was obtained that the temperature field and structural stress changes of the combustion chamber under the coupling of the temperature and working pressure through the engine thermal solid coupling simulation analysis based on the commercial software Fluent and ANSYS.The results indicated that when 40Cr was selected as material,the temperature of the shell under normal working conditions exceeded 400℃.According to the analysis of the thermal tensile test of the material,the strength of the material was greatly reduced,and the safety factor should be improved.Therefore,it was necessary to consider factors such as high temperature,high spin speed and high pressure in the design,and reasonably design the shell thickness of the combustion chamber.

关 键 词：固体火箭发动机 燃烧室 高速旋转 热强度 热固耦合 热拉伸 安全系数 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]