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碳纤维复合材料以其高强轻质等显著特点广泛应用于航天器的结构设计,以空间可展天线框架结构中的碳纤维复合材料薄壁杆件为研究对象,对其空间热辐射环境下的温度场和热变形进行数值模拟;采用分层实体单元和层合板壳单元两种模型进行计算,比较了两种尺度下的温度场和热变形结果,验证了采用层合板整体正交异性热参数和等效壳单元进行计算的适用性,进而可以为整体结构和复杂杆件的计算提供依据;同时也表明:薄壁构件的在轨温度场下的热变形水平满足空间可展天线的形面精度要求。
Carbon fiber composites are widely used in the structural design of spacecraft because of its high strength and light weight. Taking the carbon fiber composite thin-walled members in the space-extendable antenna frame structure as the research object, the temperature field And the thermal deformation were numerically simulated. The stratified solid element and the laminated plate element were used to calculate the temperature field and the thermal deformation results under two different scales. It was verified that the whole orthotropic thermal parameter and the equivalent The validity of the calculation of the effective shell element can provide the basis for the calculation of the overall structure and the complex rod; also shows that the thermal deformation level of the thin-walled component in-orbit temperature field satisfies the requirements of the surface precision of the space developable antenna .