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Development of heat pump loop thermal control system for manned spacecraft habitats

机译:用于载人航天器栖息地热泵回路热控制系统的开发

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This paper describes the performance benefits and current technology progress of an active heat pump loop (HPL) thermal control bus for spacecraft and planetary thermal control applications. Having initiated this research more than 14 years ago, this paper also briefly highlights the technical developments and obstacles overcome during this 14-year development. This paper discusses the unique features of the HPL approach that make it an attractive design choice for future manned thermal control applications: the use of a heat pump to reject heat to space at a temperature above the heat acquisition temperature, the use of non-toxic thermally stable working fluids, and the use of high-performance, lubrication-free (gravity independent) refrigeration compressors. The HPL approach has the performance benefits of a traditional two-phase pumped loop thermal bus coupled with the simplicity of a single-phase pumped loop. The HPL loop also offers the ability to achieve predetermined and isothermal cold plate operating temperatures independent of radiator temperature, and heat load. We have demonstrated that the HPL can accommodate multiple evaporative cold plates, multiple evaporation temperatures, variable thermal loads, and variable radiator temperatures. We have identified nontoxic and nonflammable working fluids that are stable under the conditions of the catalytic oxidizer used on board manned spacecraft. Two lubrication-free compressor designs have been developed and demonstrated. For small thermal loads, the HPL can use a small lubrication-free positive- displacement reciprocating compressor that is suitable for use in micro- gravity. This unique lubrication-free compressor design has already been fabricated for use in the International Space Station refrigerated centrifuge. For larger cooling loads, the HPL can use a low-vibration, long-life, compact, magnetic-bearing centrifugal compressor. The magnetic-bearing centrifugal compressor has already been demonstrated for other applications.
机译:本文介绍了用于航天器和行星热控制应用的主动热泵回路(HPL)热控制总线的性能益处和电流技术进度。在14年来之前在这项研究中启动了这项研究,还简要介绍了在这14年的发展中克服的技术发展和障碍。本文讨论了HPL方法的独特功能,使其成为未来有吸引力的热控制应用的有吸引力的设计选择:使用热泵在高于热采集温度的温度下抑制热量到空间,使用无毒热稳定的工作流体,以及使用高性能,无润滑(重力独立)制冷压缩机。 HPL方法具有传统的两相泵送环热总线的性能益处,其具有与单相泵送环的简单性相连的。 HPL环还提供了无关的散热器温度和热负荷实现预定和等温冷板操作温度的能力。我们已经证明,HPL可以容纳多个蒸发冷板,多重蒸发温度,可变热负荷和可变散热器温度。我们已经确定了在载有载物上使用的催化氧化剂的条件下稳定的无毒和不易燃的工作流体。已经开发并证明了两个无润滑的压缩机设计。对于小的热负荷,HPL可以使用适用于微重的小润滑的正置位往复式压缩机。这种独特的无润滑式压缩机设计已经制作用于国际空间站冷藏离心机。对于较大的冷却载荷,HPL可以使用低振动,长寿命,紧凑,磁性离心式压缩机。磁性离心式压缩机已经证明了其他应用。

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