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由于地球的频繁遮挡,当地球卫星在低轨道运行时,卫星的可展开天线会处在高低温交替的环境中,从而形成剧烈变化的温度场。剧烈的温度梯度变化会导致柔性较大的可展开天线发生热致振动,降低卫星全极化探测头部等关键部件的寿命。首先建立某型号卫星的物理模型,然后利用有限元法对其进行在轨时的空间瞬态热分析,得到可展开天线的温度场,将温度作为约束映射到结构仿真中,再在结构有限元模型上分析卫星的热变形,实现卫星天线热致振动的预测并为天线结构优化设计提供数据支持。对卫星模型进行热分析可以监测各时期的温度场以及预测有可能发生的热致振动,从而在不断优化设计的基础上避免这种不利的扰动。
Due to the frequent earth obstruction, when the earth satellites are in low orbit, the satellite’s deployable antenna will alternate in high and low temperatures, resulting in a drastically changing temperature field. Variations in the temperature gradient can lead to thermal-induced vibration of the flexible, deployable antenna and reduce the lifetime of key components such as the satellite’s fully-polarized detection head. Firstly, the physical model of a satellite is established, and then the transient thermal analysis of the spacecraft on-orbit is carried out by the finite element method. The temperature field of the antenna can be expanded and the temperature is used as a constraint to the structure simulation. Then, The thermal deformation of the satellite is analyzed on the model to predict the thermal induced vibration of the satellite antenna and provide data support for the antenna structure optimization design. Thermal analysis of the satellite model can monitor the temperature field over time and predict thermally induced vibrations that may occur, thereby avoiding this adverse disturbance based on continuous optimization of the design.