Abstract Cryogenic heat transport technologies are critical for integrating many space payloads. These technologies can be applied to address several payload integration issues: They allow isolation of the cryocooler from vibration-sensitive instruments, provide the ability to remotely mount the cryocooler from objects to be cooled and/or provide ability to cool remote or distributed loads. In comparison to ambient temperature heat transport, cryogenic heat transport systems are typically smaller and lighter because the heat transfer at cryogenic temperatures is one or two orders of magnitude smaller due to the typical low heat loads of the cryogenic objects being cooled. The disadvantage is often additional parasitics introduced by the cryogenic heat transport system that must be lifted by the cryocooler. An ideal cryogenic heat transport system will have high conductance and low parasitics to limit cryocooler input power in addition to meeting the typical space-flight requirements of high reliability, robustness to environmental factors, small size, and light weight. One candidate approach utilizes a single-phase gaseous heat transport loop consisting of a cryogenic circulator, transfer lines (typical rigid or flexible tubing), and compact heat exchangers. This approach was utilized in the NICMOS Cooling System that operated on the Hubble Space Telescope. This paper reviews the basic technology and presents the scaling of the technology to other temperatures and heat loads, and to multiple cooling stages.

中文翻译：

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使用气体循环的低温热传输

摘要 低温热传输技术对于集成许多空间有效载荷至关重要。这些技术可用于解决几个有效载荷集成问题：它们允许将低温冷却器与振动敏感仪器隔离，提供从要冷却的物体远程安装低温冷却器的能力和/或提供冷却远程或分布式负载的能力。与环境温度热传输相比，低温热传输系统通常更小、更轻，因为低温下的热传递由于被冷却的低温物体的典型低热负荷而小一或两个数量级。缺点通常是必须由低温冷却器解除的低温热传输系统引入的附加寄生参数。理想的低温热传输系统除了满足高可靠性、对环境因素的鲁棒性、小尺寸和轻重量等典型的太空飞行要求外，还应具有高电导率和低寄生参数，以限制低温冷却器的输入功率。一种候选方法利用由低温循环器、传输管线（典型的刚性或柔性管）和紧凑型热交换器组成的单相气体热传输回路。在哈勃太空望远镜上运行的 NICMOS 冷却系统中使用了这种方法。本文回顾了基本技术，并介绍了该技术在其他温度和热负荷以及多个冷却阶段的扩展。