低温推进剂过冷技术研究

谢福寿; 厉彦忠; 王磊; 雷刚; 邢科伟

doi:10.13224/j.cnki.jasp.2017.03.031

低温推进剂过冷技术研究

doi: 10.13224/j.cnki.jasp.2017.03.031

1.
西安交通大学能源与动力工程学院，西安 710049；航天低温推进剂技术国家重点实验室，北京 100028
2.
西安交通大学能源与动力工程学院，西安 710049
3.
航天低温推进剂技术国家重点实验室，北京 1000

基金项目: 国家自然科学基金（51376142）; 航天低温推进剂技术国家重点实验室开放课题（SKLTSCP 1610）

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出版历程
- 收稿日期: 2015-07-05
- 刊出日期: 2017-03-28

Study on subcooled technology for cryogenic propellants

摘要

摘要: 综述了低温推进剂3种过冷方式（换热过冷、抽空减压过冷和冷氦气鼓泡过冷）的过冷机理，并对比分析了其利弊，在地面全过程过冷加注时推荐采用抽空减压过冷对低温推进剂进行冷却.基于热力学理论推导了低温推进剂抽空减压过冷时耗液量、制冷量、抽空时间和泵最低抽速的表达式.研究得出低温推进剂耗液量主要用于自身温降，抵消外部漏热和贮罐材料比热容所占比例很小，如液氢自身过冷、材料比热容和外部漏热所占的相对耗液量分别为10.94%，0.38%，0.098%.推荐采用变物性算法来精确计算低温推进剂耗液量，可降低运载火箭发射成本，提高低温推进剂利用率，与现有公式对比，其相对误差为18%.
- 低温推进剂 /
- 过冷技术 /
- 抽空减压过冷技术 /
- 耗液量 /
- 抽空时间
Abstract: Three subcooled methods,including the subcooled technology of heat transfer, pumping down decompression and injecting cooled helium for cryogenic propellants were summarized. By comparing advantages and disadvantages of three methods, the subcooled technology of pumping down decompression was recommended to be used on the entire loading process of ground. Based on thermodynamics theory, expressions of consumption, refrigeration capacity, pumping down time and lowest pumping speed were derived for the subcooled technology of pumping down decompression. The researches showed that consumption of cryogenic propellants was mainly used for its temperature drop, then the proportion for offsetting external leakage heat and special heat of tank material was very small, for instance, the relative consumption of its temperature drop, special heat of tank material, and external leakage heat for liquid hydrogen was 10.94%，0.38%，0.098%, respectively. The arithmetic accurately calculating consumption of cryogenic propellants was recommended to reduce launch costs of launch vehicle and enhance utilization of cryogenic propellants. Compared with the exiting formula, its relative error was 18%.
- cryogenic propellants /
- subcooled technology /
- subcooled technology of pumping down decompression /
- liquid consumption /
- pumping down time

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参考文献(23)

[1]	谢福寿,雷刚,王磊,等.过冷低温推进剂的性能优势及其应用前景［J］.西安交通大学学报,2015,49(5):16-23.XIE Fushou,LEI Gang,WANG Lei,et al.Performance advantages and application prospects of subcooled cryogenic propellants［J］.Journal of Xian Jiaotong University,2015,49(5):16-23.(in Chinese)
[2]	杨金宁.低温推进剂的温度控制［J］.低温工程,1994(1):12-20.YANG Jinning.Temperature control of cryogenic propellants［J］.Cryogenics,1994(1):12-20.(in Chinese)
[3]	Johnson W L,Tomsik T M,Smudde T D,et al.A densified liquid methane delivery system for the Altair ascent stage［R］.AIAA-2010-1904,2010.
[4]	廖少英.低温推进剂火箭喷泉效应及其抑制［J］.上海航天,2002,19(3): 29-34.LIAO Shaoying.Geysering effect of the cryogenic propellant rocket and restraint research［J］.Aerospace Shanghai,2002,19(3):29-34.(in Chinese)
[5]	符锡理.加注过程中LO2的温升和过冷加注［J］.低温工程,1990(4):5-14.FU Xili.Temperature raise of LO2 during loading process and loading of subcooling LO2［J］.Cryogenics,1990(4):5-14.(in Chinese)
[6]	Tomsik T M，Meyer M L.Liquid oxygen propellant densification production and performance test results with a large-scale flight-weight propellant tank for the X33RLV［R］.NASA TM-216247,2010.
[7]	王瑞铨.国外运载火箭低温加注系统［J］.导弹与航天运载技术,1997(2):19-29.WANG Ruiquan.The cryogenic fueling systems of foreign launch vehicles［J］.Missiles and Space Vehicles,1997(2):19-29.(in Chinese)
[8]	章洁平.液氢加注系统［J］.低温工程,1995(4):25-28.ZHANG Jieping.Filling system of liquid hydrogen［J］.Cryogenics,1995(4):25-28.(in Chinese)
[9]	Dawson V P.Engines and innovation: Lewis Laboratory and American propulsion technology［R］.NASA SP-4306,1991.
[10]	符锡理.改善液氢液氧射前补加及时性和精确性措施的探讨［J］.航天地面设备,1990(2):20-23.
[11]	符锡理.国外航天发射场液氢液氧加注系统［J］.国外导弹与航天运载器,1984(6):40-51.
[12]	Mustafi S,Johnson W,Kashani A,et al.Subcooling for long duration in-space cryogenic propellant storage［R］.AIAA-2010-8869,2010.
[13]	周庭宇.液氧加注系统过冷器的试验研究［D］.上海：上海交通大学,2008.ZHOU Tingyu.Experimental research on subcooler of charging system of liquefied oxygen［D］.Shanghai:Shanghai Jiao Tong University,2008.(in Chinese)
[14]	Mustafi S,Canavan E,Johnson W,et al.Subcooling cryogenic propellant for long duration space exploration［R］.AIAA-2009-6584,2009.
[15]	符锡理.运载火箭液氢液氧低温推进剂加注技术［J］.低温工程,1995(6):1-8.FU Xili.A review of LH2,LO2 cryogenic propellant loading technology for launch vehicles［J］.Cryogenics,1995(6):1-8.(in Chinese)
[16]	Tomsik T M.Performance tests of a liquid hydrogen propellant densification ground support system for the X33/RLV［R］.AIAA 97-2976,1997.
[17]	符锡理.液氢的过冷加注［J］.低温工程,1988(2):52-57.FU Xili.Loading and subcooling of liquid hydrogen［J］.Cryogenics,1988(2):52-57.(in Chinese)
[18]	Larsen P S,Clark J A,Randolph W O,et al.Cooling of cryogenic liquids by gas injection［M］∥Timmerhaus K D.Advances in Cryogenic Engineering.New York:Springer,1962:507-520.
[19]	Schmidt A F.Experimental investigation of liquid hy-drogen cooling by helium gas injection［M］∥Timmerhaus K D.Advances in Cryogenic Engineering.New York:Springer,1962:521-530.
[20]	Cho N,Kwon O,Kim Y.Investigation of helium injection cooling to liquid oxygen propellant chamber［J］.Cryogenics,2006,46（2）:132-140.
[21]	Cho N,Kwon O,Kim Y.Investigation of helium injection cooling to liquid oxygen under pressurized condition［J］.Cryogenics,2006,46（11）:778-793.
[22]	Jung Y,Cho N,Baek S,et al.Heat and mass transfer of submerged helium injection in liquid oxygen vessel［J］.Cryogenics,2014,64:272-282.
[23]	布拉诺夫.液体的低温系统［M］.赵运生,崔春娥,译.北京:《低温工程》编辑部,1993.