航天推进技术研究院主办
[1]范瑞祥,田玉蓉,黄 兵.新一代运载火箭增压技术研究[J].火箭推进,2012,38(04):9-16.
FAN Rui-xiang,TIAN Yu-rong,HUANG Bing.Study on pressurization of new generation launch vehicle[J].Journal of Rocket Propulsion,2012,38(04):9-16.
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FAN Rui-xiang,TIAN Yu-rong,HUANG Bing.Study on pressurization of new generation launch vehicle[J].Journal of Rocket Propulsion,2012,38(04):9-16.
新一代运载火箭增压技术研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
38
期数:
2012年04期
页码:
9-16
栏目:
研究与设计
出版日期:
2012-08-15
- Title:
- Study on pressurization of new generation launch vehicle
- 文章编号:
- 1672-9374(2012)04-0009-08
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 随着新一代运载火箭研制的开展，新型120 t级高压补燃液氧煤油发动机将得到广泛的使用，该发动机采用的推进剂贮箱增压系统设计被列为新一代运载火箭研制的重大关键技术之一。在对国内外主要液体运载火箭增压方案进行分析的基础上对120 t级液氧煤油发动机的贮箱增压系统进行了研究，提出了液氧贮箱采用压力传感器与电磁阀组合的常温氦气加温增压，煤油贮箱采用压力传感器与电磁阀组合的常温氦气增压方案，并针对液氧贮箱采用常温氦气加温增压的方案开展了理论分析和全尺寸系统级试验研究。理论分析和试验结果表明，该增压方案可行。
- Abstract:
- With the development of new generation launch vehicles, a high pressure staged-combustion liquid oxygen/kerosene propellant rocket engine with thrust level of 120 t will be used extensively. The design of the pressurization system is one of the key technologies of new generation launch vehicles. Based on the review of pressurization system used on the domestic and foreign launch vehicles, a new tank pressurization system of launch vehicle used on the liquid oxygen/kerosene engine was studied, which used helium gas (heated helium gas in liquid oxygen tank and room temperature helium gas in kerosene tank) as the pressurization gas, and tank pressure and helium flow were controlled by tank pressure sensors and electromagnetic valves. Also a full size experimental research and theoretical analysis of heated helium pressurization system for liquid oxygen tank was conducted. The experiment and analysis results indicate that the pressurization system is feasible.
参考文献/References:
[1]廖少英. 液体火箭推进增压输送系统[M]. 北京: 国防工业出版社, 2007.
[2]STOCHL J R, MALOY J E, MASTERS A P, et al. Gaseous- helium requirements for the discharge of liquid hydrogen from a 3.96-meter-(13-fx") diameter spherical tank, NASA TN D-7019[R]. USA: NASA, 1970.
[3]TEISSIER A. Liquid helium storage for Ariane 5 main stage oxygen tank pressurization, AIAA 95-2956[R]. USA: AIAA, 1995.
[4]LACOVIC R F. Comparison of experimental and calculated helium requirements for pressurization of a centaur liquid oxygen tank, NASA TM X-2013[R]. USA: NASA, 1970.
[5]ZILLIAC G, KARABEYOGLU M A. Modeling of propellant tank pressurization, AIAA 2005-3549[R]. USA: AIAA, 2005.
[6]GRAYSON D G, ALFREDO L, CHANDLER O F, et al. Cryogenic tank modeling for the Saturn AS-203 expe- riment, AIAA 2006-5258[R]. USA: AIAA, 2006.
[7]NAOUMOU V. Simulation of high-temperature pressu- rization of liquid-propellant rocket tanks, AIAA 2009-1600[R]. USA: AIAA, 2009.
[8]STOUT P W, SNELL S A. Multiple on-off solenoid valve control for a launch vehicle propellant tank pressurization system, AIAA-99-4085[R]. USA: AIAA, 1999.
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备注/Memo
收稿日期：2012-05-17；修回日期：2012-06-13
作者简介：范瑞祥（1965—），男，博士，研究员，研究领域为运载火箭总体设计
更新日期/Last Update:
1900-01-01