CRYOGENIC PROPELLANT BOIL-OFF REDUCTION SYSTEM
CRYOGENIC PROPELLANT BOIL-OFF REDUCTION SYSTEM
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DOI：
10.1063/1.2908506
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发表时间：
2008-03
期刊：
影响因子：
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通讯作者：
D. Plachta;R. Christie;E. Carlberg;J. Feller
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文献类型：
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作者：
D. Plachta;R. Christie;E. Carlberg;J. Feller
考虑中的月球任务将受益于高比冲推进剂，如LH2和LO2，即使伴随有维持稳定燃料箱压力所必需的蒸发损失。本文介绍了一种低温推进剂蒸发减少系统，以尽量减少或消除蒸发。这样做的概念是在太空低温推进剂仓库项目下考虑的。具体来说是对大型储存库推进剂储罐的低温冷却器集成概念的研究。有一个概念被证明是有希望的——它可以通过压缩氦环有效地将热量传输到低温冷却器，即使距离很远。这方面的分析和设计被纳入美国宇航局格伦研究中心的低温分析工具。本文解释并展示了这种设计方法。分析表明，与被动低温储存相比，当LH2持续时间低至40天，LH2持续时间低至14天时，蒸发还原系统开始减少系统质量。
Lunar missions under consideration would benefit from incorporation of high specific impulse propellants such as LH2 and LO2, even with their accompanying boil-off losses necessary to maintain a steady tank pressure. This paper addresses a cryogenic propellant boil-off reduction system to minimize or eliminate boil-off. Concepts to do so were considered under the In-Space Cryogenic Propellant Depot Project. Specific to that was an investigation of cryocooler integration concepts for relatively large depot sized propellant tanks. One concept proved promising—it served to efficiently move heat to the cryocooler even over long distances via a compressed helium loop. The analyses and designs for this were incorporated into NASA Glenn Research Center's Cryogenic Analysis Tool. That design approach is explained and shown herein. Analysis shows that, when compared to passive only cryogenic storage, the boil-off reduction system begins to reduce system mass if durations are as low as 40 days for LH2, and 14 days ...