复合材料壳体固体火箭发动机温度载荷下力学响应分析  

Mechanical Response Analysis of Composite Cased SRM under Temperature Loading

作　　者：王倩 王佳兴 隋欣[1] 张亚俊[3] 王宁飞[1] WANG Qian;WANG Jiaxing;SUI Xin;ZHANG Yajun;WANG Ningfei(School of Aerospace and Engineering,Beijing Institute of Technology,Beijing 100081,C-hina;Shanghai Space Propulsion Technology Research Institute,Shanghai 201109,China;Xi'an Modern Chemistry Research Institute,Xi'an 710065,Shaanxi,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]上海航天动力技术研究所,上海201109 [3]西安近代化学研究所,陕西西安710065

出　　处：《上海航天（中英文）》2020年第6期21-29,共9页Aerospace Shanghai（Chinese&English）

摘　　要：基于非线性有限元数值仿真分析方法,使用有限元计算软件ABAQUS,分别建立金属壳体与复合材料壳体两组发动机仿真模型,分析复合材料壳体固体发动机的结构完整性,并研究复合材料壳体的各项参数对于发动机装药和壳体的应力场的影响。分析结果表明:在温度载荷下,选用复合材料壳体的端燃装药固体发动机比选用金属材料壳体的发动机具有更好的结构完整性。随着复合材料壳体厚度的增大,装药的应力、应变值均增大,壳体的应力逐渐减小;随着复合材料壳体弹性模量增大或泊松比减小,装药的应力、应变逐渐减小,而壳体的应力、应变逐渐增大。Based on the nonlinear finite element numerical simulation analysis method,the software ABAQUS is used to build solid rocket motor(SRM)simulation models with metal and composite cases. The structural integrity of composite cased SRM is analyzed,and the influence of various parameters of composite case on the stress-strain field of the grain and case is also studied. The analysis results show that under temperature loading,the end-burning SRM with composite case has better structural integrity than that with metal case. As the thickness of the composite case increases,the stress and strain of the grain increase,and the stress of the case decreases. As the elastic modulus of the composite case increases or the Poisson’s ratio decreases,the stress and strain of grain decrease,while the stress and strain of the case increase.

关 键 词：复合材料壳体 药柱 有限元 结构完整性 应力应变 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]