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本文介绍了适用于空间飞行器温控的有芯冷贮气室可变热导热管,以及这类热管的性能试验结果,并与平面交界面理论、扩散交界面理论的计算结果作了比较,两者均符合得较好。文中通过近似地计算交界区的长度,对平面交界面理论进行了修正,从而确定了既简便又有一定精确度的设计方法。此种热管是空间飞行器温控的一种较为先进的技术。本文还介绍了一个拟用于空间飞行器进行飞行试验的可控热管辐射器的试验器。
In this paper, we introduce the variable thermal conduction heat pipe for a c-type core cold storage chamber which is suitable for spacecraft temperature control and the performance test results of the heat pipe. Comparing with the calculation results of the plane interface theory and the diffusion interface theory, two Who are in line with better. In this paper, by calculating the length of the junction area approximately, the theory of plane interface is modified, and the design method which is both simple and accurate is determined. This kind of heat pipe is a more advanced technology of spacecraft temperature control. This article also introduces a tester for a controlled heat pipe radiator to be used in flight tests of spacecraft.