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[1]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(01):1-7.
　LI Bin,ZHANG Xiaoping,GAO Yushan.Consideration on development of reusable liquid rocket engine in China[J].Journal of Rocket Propulsion,2017,43(01):1-7.
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我国可重复使用液体火箭发动机发展的思考

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 43 期数: 2017年01期 页码: 1-7 栏目: 专论与综述 出版日期: 2017-04-01
Title:
Consideration on development of reusable liquid rocket engine in China
作者:
李斌1; 张小平2; 高玉闪2
1. 航天推进技术研究院，陕西 西安710100；2. 西安航天动力研究所, 陕西 西安 710100
Author(s):
LI Bin1;  ZHANG Xiaoping2;  GAO Yushan2
1. Academy of Aerospace Propulsion Technology, Xi’an 710100, China; 2. Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
关键词:
重复使用; 液体火箭发动机; 推进剂; 推力; 关键技术
Keywords:
reusability; liquid rocket engine; propellant; thrust; key technology
分类号:
V434-34
文献标志码:
A
摘要:
重复使用是降低航天发射成本的重要途径之一,是液体火箭发动机未来发展的重要方向.本文分析了可重复使用液体发动机的发展趋势,针对可重复使用运载器对发动机功能的需求,探讨了动力系统方案;对比了液氧煤油和液氧甲烷等推进剂组合和不同循环方式,认为几种发动机方案均可满足重复使用运载器的需求;研究了重复使用发动机的关键技术,提出应重点研究可重复使用液体火箭发动机高温组件热结构疲劳寿命评估及延寿技术、运动组件摩擦磨损技术、结构动载荷控制与评估技术、快速检测评估与维修维护技术、健康监控与故障诊断技术、二次或多次起动技术与大范围推力调节技术等.
Abstract:
Reusability is an important way to reduce the cost of space launch,and is an important direction for the future development of liquid rocket engine.The development tendency of reusable liquid rocket engine is described in this paper.The power systems are discussed according to the demands of engine functions of the reusable launch vehicle (RLV).The combination of LOX/Kerosene and LOX/Methane propellants as well as their different cycle modes are compared.It is found according to the comparison that all these mentioned above can meet the needs of RLV.The key technologies of the reusable engine were studied,which indicates that the assessment technologies for thermal fatigue of high-temperature engine components,motion assembly friction and wear,structural dynamic load control,rapid detection of repair and maintenance,health monitoring,fault diagnosis secondary or multi-start,and wide-range thrust modulation should be researched emphatically.

参考文献/References:

[1]曹志杰. 国外可重复使用运载器近期进展[J]. 国际太空,2005 (10): 20-25.
[2]DAVIS J A, CAMPBELL R L. Advantages of a full-flow staged combustion cycle engine system: AIAA 97-3318 [R]. USA: AIAA, 1997.
[3]Anon. High performance Russian NK-33 LOX/Kerosene liquid rocket engine: AIAA 94-3397[R]. USA: AIAA, 1994.
[4]ROBERT E M, ANTHONY P T. A status report on the development of the Kistler aerospace K-1 resuable launch vehicle: AIAA 2001-2069[R]. USA: AIAA, 2001.
[5]于霞, 孙伶俐, 单文杰. 国外可重复使用运载器发展现状和趋势[J]. 国际太空, 2012 (12): 2-6.
[6]GORACKE B D, LEVACK D J. Tripropellant engine drive cycle considerations for the SSTO application: AIAA 95-2950[R]. USA: AIAA, 1995.
[7]禹天福, 李亚裕. 液氧甲烷发动机的应用前景[J]. 航天制造技术, 2007, 4(2): 1-4.
[8]李斌, 张小平, 马冬英. 我国新一代载人火箭液氧煤油发动机[J]. 载人航天, 2014, 20(5): 427-431.
[9]高朝辉, 刘宇, 肖肖, 等. 垂直着陆重复使用运载火箭对动力技术的挑战[J]. 火箭推进, 2015, 41(3): 1-6. GAO Zhaohui, LIU Yu, XIAO xiao, et al. Challenge to propulsion technology for vertical landing reusable launch vehicle[J]. Journal of rocket propulsion, 2015, 41(3): 1-6.
[10]杨勇. 我国重复使用运载器发展思路探讨[J]. 导弹与航天运载技术, 2006, 284(4): 1-4.
[11]BURKHARDT H, SIPPEL M, HERBERTZ A, et al. Effects of the choice between kerosene and methane on size and performance of reusable liquid booster stages: AIAA 2003-5122[R]. USA: AIAA , 2003.

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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(01):14.

备注/Memo

收稿日期：2016-07-03；修回日期：2016-07-11 作者简介：李斌（1969—），男，研究员，研究领域为液体火箭发动机

更新日期/Last Update: 1900-01-01