低温推进剂长时间在轨的蒸发量控制技术进展  

Progress of Study on Transpiration Control Technology for Orbit Long-term Applied Cryogenic Propellant

作　　者：胡伟峰[1] 申麟[1] 杨建民[1] 赫武乐[1] 

机构地区：[1]中国运载火箭技术研究院研究发展中心,北京100076

出　　处：《导弹与航天运载技术》2009年第6期28-34,共7页Missiles and Space Vehicles

摘　　要：低温推进剂特别是液氢和液氧组合是目前性能最高的化学推进剂,也是NASA未来月球、火星探测乃至更远距离的深空探测的首选推进剂[1]。但低温推进剂长时间在轨应用主要受限于低沸点的推进剂受热蒸发所带来的贮箱压力控制[2]和蒸发损失等一系列问题,其核心是低温推进剂的蒸发量控制问题。本文从被动防护和主动制冷等方面对国外低温推进剂蒸发量控制技术的研究进行了分类归纳,并对低温推进剂蒸发量控制技术进行了总结和展望。Cryogenic propellant, especially the LH2/Lox combination, is the chemical propellant with highest impulse currently, and also the first choice for NASA＇s lunnar, mars and deep space exploration. But the application of cryogenic propellant has been limited by the pressure control of tank and loss caused by transpiration. Transpiration control is the crucial part of the application orbit long-term applied cryogenic propellant. From the aspects of passive insulation technology and active technology, the abroad transpiration control technologies for cryogenic propellant are summarized, and some conclusion and suggestion on transpiration control technologies for cryogenic propellant are proposed.

关 键 词：低温推进剂 蒸发量控制 低温制冷机 

分 类 号：V511.6[航空宇航科学与技术—航空宇航推进理论与工程]