PDF下载 分享
[1]潘一力,周海清,吉 林,等.液氧/液甲烷姿控发动机点火技术研究[J].火箭推进,2019,45(04):16-25.
　PAN Yili,ZHOU Haiqing,JI Lin,et al.Study on ignition technology of LOX/LCH4 attitude control engine[J].Journal of Rocket Propulsion,2019,45(04):16-25.
点击复制

液氧/液甲烷姿控发动机点火技术研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 45 期数: 2019年04期 页码: 16-25 栏目: 研究与设计 出版日期: 2019-08-30
Title:
Study on ignition technology of LOX/LCH4 attitude control engine
文章编号:
1672-9374(2019)04-0016-10
作者:
潘一力; 周海清; 吉 林; 许宏博
(上海空间推进研究所 上海空间发动机工程技术研究中心,上海 201112)
Author(s):
PAN Yili; ZHOU Haiqing; JI Lin; XU Hongbo
(Shanghai Engineering Research Center of Space Engine,Shanghai Institute of Space Propulsion,Shanghai 201112,China)
关键词:
液氧/液甲烷;  电点火;  激光点火;  姿控发动机
Keywords:
liquid oxygen and liquid methane;  electric ignition;  laser ignition;  attitude control engine
分类号:
V439
文献标志码:
A
摘要:
液氧/液甲烷推进剂组合具有高比冲性能以及其他优异的综合使用性能,已经成为未来空间化学推进的重要发展方向之一。点火技术作为液氧/液甲烷姿控发动机的重大关键技术,对发动机可靠启动、响应特性、脉冲一致性等关键指标具有重要影响。欧美国家已经开展系统以及相关组件的预先研究,其中美国已经完成了系统级的地面自由飞行试验。国内也已开展了低温推进系统技术论证,并开展了主发动机、姿控发动机以及点火器、低温贮箱、低温阀门等关键组件的研发。针对液氧/液甲烷低温推进剂组合进行了点火技术分析筛选和试验研究,验证了电火花点火与激光诱导等离子点火两种方案的原理可行性。试验表明在入口条件从气态到液态的宽广范围内两种方案均能实现可靠、可重复点火,两种点火方式对于LOx/LCH4发动机均原理可行。试验得出可靠点火的火花能量边界特性、混合比边界特性、响应特性以及脉冲特性,为后续液氧甲烷发动机设计提供依据。
Abstract:
In recent years,the propellant combination of liquid oxygen/liquid methane(LOX/LCH4)has become one of the important development directions of space chemical propulsion in the future due to its high specific impulse and excellent comprehensive performance.As a crucial technology of LOX/LCH4 attitude control engine,the ignition technology has an important influence on the starting reliability,response characteristics and impulse consistency of the engine.American and European countries have focused on the system integration and component technologies for the past few years,in which the United States has successfully conducted the system-level free flight test of LOX/LCH4 propulsion system.Technical demonstration of cryogenic propulsion system has been carried out in China,and research and development of main engine,attitude control engine and key components such as igniter,cryogenic tank and cryogenic valve have been conducted.In this paper,the ignition technology of LOX/CH4 attitude control engine was analyzed,screened and tested,and the feasibility of electric spark ignition and laser induced plasma ignition was verified.The experimental results show that both schemes can achieve reliable and repeatable ignition in a wide range of inlet conditions from gaseous phase to liquid phase,which prove that both ignition methods are feasible for LOX/CH4 engine.The boundary characteristics of spark energy,boundary characteristics of mixing ratio,response characteristics and impulse characteristics of reliable ignition are obtained,which provide a basis for the subsequent design of LOX/CH4 rocket engine.

参考文献/References:

[1] NASA’s exploration systems architecture study,final report:NASA-TM-2005-214062[R].USA:NASA,2005.
[2] TIMOTHY D S,MARY F W.Liquid oxygen/liquid methane propulsion and cryogenic advanced development[C]//International Aerospace Conference.[S.l.]:[s.n.],2008.
[3] HURLBERT E A,ATWELL M J,MELCHER J C,et al.Integrated pressure-fed liquid oxygen / methane propulsion systems - morpheus experience,MARE,and future applications[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:American Institute of Aeronautics and Astronautics,2016.
[4] HART J. Vertical test bed flight testing:NASA-TM-2014[R].USA:NASA, 2014.
[5] OLANSEN J B, MUNDAY S R, Project morpheus: lander technology development [C]//AIAA Space Conference and Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics,2014.
[6] HERLBURT E, ANGSTADT T, 870lbf reaction control system tests using LOX/ethanol and LOX/methane at white sands test facility[C]// 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics,2008.
[7] ROBINSON P J, VEITH E M, LINNE D L, et al. Conceptual design of a 5,500-lbf LOX/LCH4 lunar ascent main engine[C]//4th JANNAF Liquid Propulsion Subcommittee Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics,2008.
[8] HART J.Vertical test bed flight testing:NASA-TM-2014[R].USA:NASA,2014.
[9] OLANSEN J B,MUNDAY S R.Project morpheus:lander technology development[C]//AIAA Space Conference and Exposition,[S.l.]:AIAA,2014.
[10] 李春红,张小平,马冬英,等.液氧/甲烷燃气发生器点火方案研究[J].火箭推进,2010,36(5):7-12.LI C H,ZHANG X P,MA D Y,et al.Ignition scheme of LOX/methane gas generator[J].Journal of Rocket Propulsion,2010,36(5):7-12.
[11] 高玉闪,杜正刚,金平,等.气氧/甲烷同轴剪切喷注器燃烧特性数值模拟[J].火箭推进,2009,35(5):18-23,33.GAO Y S,DU Z G,JIN P,et al.Numerical simulation on the combustion characteristic of shear coaxial GO2/ GCH4 injector[J].Journal of Rocket Propulsion,2009,35(5):18-23,33.
[12] 孙宏明.液氧/甲烷发动机评述[J].火箭推进,2006,32(2):23-31.SUN H M.Review of liquid oxygen/methane rocket engine[J].Journal of Rocket Propulsion,2006,32(2):23-31.
[13] 李斌,张小平,高玉闪.我国可重复使用液体火箭发动机发展的思考[J].火箭推进,2017,43(1):1-7.LI B,ZHANG X P,GAO Y S.Consideration on development of reusable liquid rocket engine in China[J].Journal of Rocket Propulsion,2017,43(1):1-7.
[14] 王珺,张卫红,石文靓,等.60 t级液氧/甲烷发动机起动过程建模与仿真[J].火箭推进,2013,39(5):16-22.WANG J,ZHANG W H,SHI W J,et al.Modeling and simulation of start-up process of 60 t class LOX/methane liquid rocket engine[J].Journal of Rocket Propulsion,2013,39(5):16-22.
[15] BREISACHER K,AJMANI K.LOX / methane main engine igniter tests and modeling[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virigina:American Institute of Aeronautics and Astronautics,2008.
[16] KLEINHENZ J,SARMIENTO C,MARSHALL W.Experimental investigation of augmented spark ignition of a LO2/LCH4 reaction control engine at altitude conditions:NASA/TM.2012-217611[R].USA:NASA,2012.
[17] WILLIAM M,KLEINHENZ J E.Analysis of 100-lbf(445-N)LO2-LCH4 reaction control engine impulse bit performance:NASA/TM.2012-217613[R].USA:NASA,2012.
[18] LARRY C,LIOU L.Laser ignition in liquid rocket engine[C]// 30th AIAA/SAE/ASME/ASEE Joint Propulsion Conference & Exhibit.Indianapolis,IN:AIAA,1994.
[19] KUMAKAWA A,KUSAKA K,SATO M,et al.Experimental study on a laser ignited thruster made of Si3Ni4[C]//40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virigina:American Institute of Aeronautics and Astronautics,2004.
[20] IIZUKA T,BESNARD E,NAGATA T.Numerical simulation of LOX/methane glow plug ignition system[C]//47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Reston,Virigina:American Institute of Aeronautics and Astronautics,2011.
[21] LAWVER B,ROUSAR D,BOYD W.Ignition characterization of the GOX/ethanol propellant combination[C]//20th Joint Propulsion Conference.Reston,Virigina:American Institute of Aeronautics and Astronautics,1984.

相似文献/References:

[1]金宝志,申连华,李国岫,等.不同组份下硝酸羟胺基液体推进剂电点火及稳定燃烧[J].火箭推进,2024,50(05):96.[doi:10.3969/j.issn.1672-9374.2024.05.009]
　JIN Baozhi,SHEN Lianhua,LI Guoxiu,et al.Electric ignition and stable combustion of hydroxylamine nitrate-based liquid propellant for different components[J].Journal of Rocket Propulsion,2024,50(04):96.[doi:10.3969/j.issn.1672-9374.2024.05.009]

备注/Memo

收稿日期:2018-07-28; 修回日期:2018-10-19基金项目:上海市空间发动机工程技术研究中心资助项目(17DI2280800)作者简介:潘一力(1987—),男,硕士,研究领域为液体火箭发动机、推进系统设计

更新日期/Last Update: 2019-08-31