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针对某航天机构加载驱动部件提出了一种热变形分析计算方法.利用MARC软件建立了加载驱动部件的有限元模型,通过瞬态传热分析计算出该系统随时间变化的温度场及其他热参数.分别提取10,20,30 min时的加载驱动部件内部温度分布情况,生成温度场文件,并以此作为热载荷进一步求解出各时刻加载驱动部件内的热应力和变形值.分析所得结果可以用作进一步修改和优化航天机构加载驱动部件设计的依据.
A thermal deformation analysis and calculation method is proposed for loading a driving mechanism of a space agency.The finite element model of the driving component is established by using MARC software and the temperature field and other thermal parameters of the system are calculated by transient heat transfer analysis .The temperature distributions of the load-driven components were extracted respectively at 10, 20, 30 min to generate the temperature field file, which was used as the thermal load to further solve the thermal stress and deformation values of the loaded drive components at each time.The results of the analysis could be Used as a basis for further revising and optimizing the design of the aerospace agency’s load-driven components.