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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。
Aiming at the fault condition of SADA axis of geostationary orbit satellites, which is caused by overlarge temperature gradient in the circumferential or axial direction, the thermal design of a SADA satellite, thermal simulation and solar simulator illumination test are carried out. Thermal design using a light barrier and average temperature measures to reduce the SADA temperature gradient and external heat flow effects. The external heat flow simulates the winter solstice working condition and the cabin boundary temperature is 25 ℃. By arranging 88 temperature measuring points inside and outside, the cable harness, power disk and brush in SADA are obtained with high temperature. The maximum circumferential temperature difference between the two shaft ends is 1.2 ℃ and 8 ℃ respectively, and the maximum temperature difference between the two shaft ends is 6.8 ℃. In this temperature environment, SADA is working properly, proving the rationality of its own and thermal control design. Thermal simulation results are in good agreement with the experimental results. The results have also been verified in orbit data. SADA mathematical models, test methods, and results provide thermal design guidance for SADA working with subsequent models under different operating conditions.