Thermal design of SADA and its detailed temperature distribution in HT condition for geostationary orbit satellite
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摘要: 针对地球静止轨道卫星SADA轴系周向或轴向温度梯度过大导致卡死的故障情况，开展某卫星SADA热设计、热仿真及太阳模拟器光照试验研究。采用挡光板及均温措施等热设计减小SADA温度梯度及外热流影响。试验外热流模拟冬至工况，舱内边界温度25℃，通过在其内部和外部布置88个温度测点，得出SADA内部的电缆束、功率盘片及电刷温度较高。轴系两端面周向最大温差分别为1.2℃和8℃，轴系两端面最大温差6.8℃。在此温度环境下，SADA工作正常，证明了其本身及热控设计的合理性。热仿真计算结果与试验结果一致性较好。研究结果还得到了在轨数据的验证。SADA数学模型、试验方法和结果可为后续型号不同工况条件工作的SADA提供热设计指导。Abstract: The large temperature gradient in the circumferential and axial directions of the bearing can lead to a seizure failure. The thermal design, the thermal simulation and the thermal vacuum experiment based on solar simulator are carried out, and the detailed temperature distribution of the SADA is obtained. The light barrier and the temperature uniformity measures are taken to reduce the temperature gradient and the influence of the external heat flux. In the thermal experiment, the external heat flux is the same as that in the winter solstice. The boundary temperature of the cabin plates is 25℃. Eighty-eight thermal couples are installed to collect the temperature data for the SADA. The bunch of cables, the slip ring assembly and the electrical brushes are the locations with higher temperature. The maximum temperature differences are 1.2℃ and 8℃ on the head face and the end face of the bearing in the circumferencial direction. The maximum temperature difference is 6.8℃ between the head face and the end face of the bearing in the axial direction. The SADA can work well under these temperature conditions. It is shown that the SADA design and the thermal control design are reasonable. The results of the thermal simulation are consistent with the experiment results. The results are also verified by the on-orbit data. The thermal analysis model, the experimental methods and the test results can be used in the subsequent thermal designs and the temperature distribution researches of the SADA under different working conditions.
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