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为解决排热功率剧烈变化的航天器大功率组件的温度控制问题,提出了小型热电泵相变材料热控系统。通过实验研究了5种不同设计方案下大功率组件的温度波动情况,其中将大功率组件置于相变材料容器和热电泵之间的方案最佳,能有效降低大功率组件最高温度和温度波动幅度,其最低温度为24.5℃,最高温度为55.2℃。研究了大功率组件在向阳期间和阴影期间工作的两种模式对温度波动的影响,发现前者更有利于降低大功率组件的最高温度和温度波动幅度。结果表明,采用该热控系统对航天器短时大功率组件进行温度控制是可行的。
In order to solve the problem of temperature control of spacecraft high-power components with drastic changes of exhaust heat power, a thermal control system of phase change material for small thermoelectric pump was proposed. The temperature fluctuation of high-power components under five different design schemes is studied experimentally. The best solution is to dispose the high-power components between the phase-change material container and the thermoelectric pump, which can effectively reduce the maximum temperature and temperature fluctuations of the high-power components Amplitude, the minimum temperature of 24.5 ℃, the maximum temperature of 55.2 ℃. The influence of two modes of high-power module operating in sunny and shadowing periods on the temperature fluctuation is studied. The former is more conducive to reducing the maximum temperature and the fluctuation of temperature in the high-power component. The results show that it is feasible to use this thermal control system to control the temperature of spacecraft short-time high power module.