航天推进技术研究院主办
[1]张小平,李春红,马冬英.液氧／甲烷发动机动力循环方式研究[J].火箭推进,2009,35(04):14-20.
Zhang Xiaoping,Li Chunhong,Ma Dongying.Study on the LOX／methane rocket engine power cycles[J].Journal of Rocket Propulsion,2009,35(04):14-20.
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Zhang Xiaoping,Li Chunhong,Ma Dongying.Study on the LOX／methane rocket engine power cycles[J].Journal of Rocket Propulsion,2009,35(04):14-20.
液氧／甲烷发动机动力循环方式研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
35
期数:
2009年04期
页码:
14-20
栏目:
研究与设计
出版日期:
2009-08-28
- Title:
- Study on the LOX／methane rocket engine power cycles
- Keywords:
- liquid rocket engine; LOX／methane; nontoxic propellant; reusable; power cycle
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 综述了液氧／甲烷发动机的研究进展．分析了液氧／甲烷发动机的特性和应用前 景，对比了大推力液氧／甲烷发动机的动力循环方式，提出发动机动力循环方式选择应综合用 途、性能、研制难度及使用成本等多方面因素，一次性使用的发动机应采用高性能的高压补 燃循环。其中部分甲烷冷却推力室的富燃补燃循环较佳；重复使用的发动机应根据工作次数 和工作寿命，重点考虑系统压力低的燃气发生器循环和低压的补燃循环。
- Abstract:
- Development of LOX／methane rocket engine was described in this paper．The characteristic and potential use were analyzed．Different power cycles of high thrust engine was compared． The application，the performance，the difficulties in developing and the cost all should be considered for the choice of power cycles．High pressure staged combustion cycle with high performance should be used for expandable engines，and the fuel-rich staged combustion cycle with partial methane cooling chamber is the best．Gas generation cycle and low pressure staged combustion cycle should be considered to use for reusable engines according to operating times and operating life．
参考文献/References:
[l]孙宏明．液氧／甲烷发动机评述[J]．火箭推进，2006，32
(2)：23-31．
[2]Philippart K D，Moor M D．Stability Analyses of Liquid Oxygen／Methane Injectors Using Currently Available
AnM”icM Tools[R]．AIAA88-285 1．
[3]Judd D，Buccella S。Alkema M，et a1．Development
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[R]．AIAA 2006-5079．
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[5l Leudiere V，Supie P，Beaurain A，et a1．KVD-1 Engine
in LOX／CH4[R]．AIAA 2007—5446．
[6]Zurbach S，Thomas J L Recent Advances on LOX／
Methane Combustion for Liquid Roket Engine Rejector[R]．
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[7]Torano Y，Afita M，Takahashi H，et a1．Current Study
Status of the Advanced Technologies for the J—I Upgrade
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1783．
[8]Kim K，Ju D．Development of Chase-10 Liquid Rocket
Enne Having 10ft Thrust Using L02＆LNG(Methane)
[R]．AIAA 2006--4907．
[9]张小平，丁丰年．我国载人登月重型运载火箭动力系统
探讨[J]．火箭推进，2009，35(2)：1—6．
[10]王鹏武．全流量补燃循环液氧／甲烷发动机系统分析
[J]．火箭推进，2004，30(6)：15-18。
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备注/Memo
收稿日期：2009--06—08；修回日期：2009-07—14。 作者简介：张小平(1970一)，男，高级T程师，研究领域为液体火箭发动机系统设计。
更新日期/Last Update:
1900-01-01