论文部分内容阅读
传统星载桁架结构需通过驱动器实现展开/收拢动作,应用形状记忆复合材料可突破该限制。对新型可展桁架各组件进行热控方案设计,基于I-DEAS/TMG软件建立热分析数值模型,对桁架各组件在轨外热流以及温度场变化进行计算分析。结果表明:最外端桁架在轨运行4个周期后其温度场呈周期性变化特征;不同多层隔热材料(multi-layer insulation material,MLI)表面辐射特性对内/外端纵杆温度影响明显;热控方案能实现有效的在轨温度控制。
The traditional space truss structure needs to be expanded / shrunk by a driver, and shape memory composite materials can overcome this limitation. The thermal control scheme of the new displayable truss components was established. Based on I-DEAS / TMG software, a numerical model of thermal analysis was established, and the on-orbit heat flow and temperature field of truss components were calculated and analyzed. The results show that the temperature field of the outermost truss changes periodically after 4 cycles of orbital operation. The influence of surface radiation characteristics of different multi-layer insulation materials (MLI) on the temperature of the inner / outer longitudinal beams Obvious; thermal control scheme enables effective in-orbit temperature control.