航天器
发射率
材料科学
温度控制
振幅
热电冷却
壳体(结构)
传热
信号(编程语言)
温度测量
航空航天工程
热辐射
光学
工程类
机械
物理
热电效应
复合材料
计算机科学
热力学
程序设计语言
作者
Haitao Hu,Shoujin Chang,Yang Li,Xuan Li
标识
DOI:10.1016/j.ijrefrig.2022.12.007
摘要
The temperature control precision is crucial for the sensitive elements in a spacecraft. In the present study, a temperature control system to improve the performance of spacecraft precision instruments was designed and experimentally investigated. In the temperature control system, heat pipes, high emissivity coatings, and semiconductor coolers are applied to dissipate the internal heat and control the temperature of a sensitive element. Heat pipes are arranged on the sensitive element and the innermost shell, high radiation coatings are sprayed on each shell surface to transfer the heat to the outer layer, and semiconductor coolers are mounted on the outermost shell and dissipate heat to the external environment. The temperature of the sensitive element is compensated by an electric heating device to reduce the temperature fluctuations. A digital-analog control scheme was designed to maintain the temperature of the outer shell and the sensitive component of the temperature control system. The control accuracy of the temperature control system is within ±0.1 ℃ under different working conditions. When the frequency point is at 0.089928 Hz, the signal amplitude of temperature is taken as the maximum value of 5.05 mK; the amplitude spectral density is 0.006 ∼ 9 mK/Hz1/2 in the frequency range 0.001 ∼ 0.25 Hz.
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