航天推进技术研究院主办
[1]杨成虎,林庆国,刘昌国.高性能液体远地点发动机技术发展[J].火箭推进,2013,39(04):1-7.
YANG Cheng-hu,LIN Qing-guo,LIU Chang-guo.Technology development of high-performance liquid apogee engine[J].Journal of Rocket Propulsion,2013,39(04):1-7.
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YANG Cheng-hu,LIN Qing-guo,LIU Chang-guo.Technology development of high-performance liquid apogee engine[J].Journal of Rocket Propulsion,2013,39(04):1-7.
高性能液体远地点发动机技术发展
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年04期
页码:
1-7
栏目:
专论与综述
出版日期:
2013-08-30
- Title:
- Technology development of high-performance liquid apogee engine
- 文章编号:
- 1672-9374(2013)04-0001-07
- 关键词:
- 高性能液体远地点发动机; 喷注器; 燃烧室; 耐高温材料
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 液体远地点发动机的性能提高具有显著的经济效益和社会效益。通过使用高性能喷注器、高效燃烧室和新型耐高温材料，国外采用N2O4/MMH推进剂的液体远地点发动机最高比冲已达到323 s。分析了国外高性能液体远地点发动机性能特点和关键技术，介绍了我国第3代490 N发动机的研制情况，结合工程应用要求和研制现状，提出了第3代490 N发动机的后续研究重点。
- Abstract:
- The performance improvement of liquid apogee engine (LAE) can create enormous economic and social benefits. The maximum specific impulse of foreign N2O4/MMH LAE with high-performance injector, efficient combustion chamber and new type high-temperature resistant material is up to 323 s. In this paper, the characteristics and key technologies of the high-performance LAE abroad are analyzed and the development of the Third Generation 490 N engine in china is introduced. According to the engineering need and the development status of the engine, the research focus of the Third Generation 490 N engine is put forward.
参考文献/References:
[1]刘昌国, 张中光, 韩宏印, 等: 高比冲双组元液体远地点火箭发动机研究[J]. 上海航天, 2003 (4): 30-33.
[2]HENDERSON S, STECHMAN C, WIERENGA K, et al. Performance results for the advanced materials bipropel- lant rocket (AMBR) engine, AIAA 2010-6883[R]. USA: AIAA, 2010.
[3]KRISMER D A D, MILLER S, STECHMAN C, et al. Qualification testing of a high performance bipropellant rocket engine using MON-3 and hydrazine, AIAA 2003-4775[R]. USA: AIAA, 2003.
[4]ARIKAWA Y, ARAKI T. Wideband Inter-Networking en- gineering test and demonstration satellite propulsion sys- tem and engineering model test results, AIAA 2006-4691 [R]. USA: AIAA, 2006.
[5]STECHMAN R C, SUMPTER D. Development history of the apollo reaction control system rocket engine, AIAA 89-2388[R]. USA: AIAA, 1989.
[6]STECHMAN C, KRISMER D. Off-limit testing of the model R-4D 110 lbf (490N) bipropellant rocket engine, AIAA-2004-3694[R]. USA: AIAA. 2004.
[7]STECHMAN C, WOLL P, FULLER R. A high perfor- mance liquid rocket engine for satellite main propulsion, AIAA 2000-3161[R]. USA: AIAA, 2000.
[8]WU P K, WOLL P, STECHMAN C, et al. Qualification testing of a 2nd generation high performance apogee thruster, AIAA 2001-3253[R]. USA: AIAA, 2001.
[9]JASSOWSKI D M, SCHOENMAN L. Advanced small rocket chambers option 3-110 lbf Ir-Re Rocket, Volume I[R]. USA: NASA, 1995.（下转第40页）
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备注/Memo
收稿日期：2012-01-25；修回日期：2012-03-24
基金项目：国家863项目（2009／AA705308）
作者简介：杨成虎（1978—），男，高级工程师，研究领域为液体火箭发动机设计
更新日期/Last Update:
1900-01-01