在对低温推进剂在轨贮存技术简要概述的基础上,针对推进飞行器的2种构型,提出了3种低温推进剂在轨贮存被动蒸发控制方案,建立了技术方案中复合绝热结构和蒸汽冷却屏的传热分析模型,对不同轨道、不同构型和多个蒸发控制方案的低温贮箱漏热量和蒸发量进行了计算和分析.结果表明,绝热结构隔热性能为0.05 W/(m2·K)时,被动蒸发控制方案可控制液氢贮箱蒸发率为0.4％～1.1％/天;近地轨道低温贮箱的蒸发量明显大于地月转移轨道的蒸发量;蒸汽冷却屏可以明显减小低温贮箱的漏热;随着绝热结构隔热性能的增加,低温贮箱的漏热量减小.%The long-term storage technology for cryogenic propellent was briefly summarized and three passive boil off control schemes for orbital storage of cryogenic propellant were presented for two configurations of orbital transfer spacecrafts. The heat transfer analysis model was established for the composite insulation structure and the vapor cooling shield. The calculation and analysis of heat-leak rate and boil-off losses were conducted with different schemes, different orbits and different configurations. The results showed that the boil-off rate could be controlled within 0. 4％ ～1. 1％/day for LH2 tank when the insulation performance was 0. 05 W/( m2·K) , the boil-off losses of cryo-genic tank in low earth orbit was more than that in the earth-moon transfer orbit, the vapor cooling shied could significantly decrease the heat-leak of cryogenic tank, while the heat-leak of cryogenic tank decreased with the increase of the insulation performance of the composite insulation structure.
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