高灵敏度光学探测模块热设计

Thermal Design of High-Sensitivity Optical Detection Module

高灵敏度光学探测模块(简称探测模块)工作时总功耗高达600W,为了使模块满足正常工作时的温度要求,解决探测模块散热困难的问题,提出了一种主动热控与被动热控相结合的热设计方法。首先对探测模块所处的外部空间环境及内热源进行了分析,然后对探测模块进行了热设计;并对所设计的方案进行了有限元仿真分析,得到了探测模块不同工况在不同边界温度下的温度分布数值。分析结果表明,上述探测模块工作温度大约在2.27℃~6.50℃之间,热分析计算的结果验证了所提出热设计方法的合理性,证明了所提的热设计方法能够有效的解决大功耗航天器的散热问题,对今后大功耗航天器的热控设计具有一定的借鉴和指导意义。

The high-sensitivity optical detection module(detection module for short)has a total power consumption of up to 600W when working.In order to make the module meet the temperature requirements during normal operation and solve the problem of difficult heat dissipation of the detection module,this paper proposes a combined thermal design method of both active thermal control and passive thermal control.This paper first analyzed the external space environment and internal heat source where the detection module is located,and then conducted a thermal design on the detection module.Then a finite element simulation analysis was conducted on the designed scheme,and the temperature distribution of the detection module was obtained in different working conditions at different boundaries.The analysis results show that the working temperature of the detection module is about 2.27℃C~6.50℃.The results of thermal analysis and calculation verify the rationality of the proposed thermal design method and prove that the proposed thermal design method can effectively solve the large power consumption.The heat dissipation problem of spacecraft has certain references and guiding significance for the thermal control design of spacecraft with high power consumption in the future.