航天推进技术研究院主办
[1]赵 婷,陈夏超,杨成虎,等.面向高轨卫星的液体轨控发动机研制进展[J].火箭推进,2018,44(01):1-7.
ZHAO Ting,CHEN Xiachao,YANG Chenghu,et al.Developing progress of liquid bipropellant orbit control engine for high orbit satellite[J].Journal of Rocket Propulsion,2018,44(01):1-7.
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ZHAO Ting,CHEN Xiachao,YANG Chenghu,et al.Developing progress of liquid bipropellant orbit control engine for high orbit satellite[J].Journal of Rocket Propulsion,2018,44(01):1-7.
面向高轨卫星的液体轨控发动机研制进展
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年01期
页码:
1-7
栏目:
专论与综述
出版日期:
2018-02-28
- Title:
- Developing progress of liquid bipropellant orbit control engine for high orbit satellite
- 文章编号:
- 1672-9374(2018)01-0001-07
- Keywords:
- high orbit satellite; orbit control engine; specific impulse performance; research progress
- 分类号:
- V439.7-34
- 文献标志码:
- A
- 摘要:
- 综述了面向高轨卫星的液体轨控发动机发展及现状,简要介绍了490 N轨控发动机从第一代、第二代到第三代发展历程,着重阐述了高性能750 N轨控发动机的研制情况,并介绍了其技术方案及试验结果,总结了国内星用轨控发动机的研制经验。我国当前技术状态下,采用铌合金材料燃烧室可实现的750 N轨控发动机真空比冲性能可达到321 s以上,同时工作寿命满足25 000 s的工程需要,与国外高性能液体轨控发动机性能比对可见,我国面向高轨卫星用750 N发动机达到国际先进水平。
- Abstract:
- The development and status quo of liquid orbit control engine for high orbit satellite is summarized.The development course(the first generation, the second generation to the third generation)of the 490 N orbit control engine is introduced briefly in this paper.The development status, technical solution and test result of 750 N high-performance orbit control engine are described.Development experience of orbit control engine for satellite in China is summarized.According to current technical state of China, the specific impulse of the 750 N orbit control engine with niobium alloy combustor can reach more than 321 s, and its working life can meet the requirements of 25 000 s.Compared with the high-performance liquid orbit control engines in foreign countries, the 750 N engine used for high orbit satellite has reached the international advanced level.
参考文献/References:
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[2] SCHULTE G. High performance 400 N MMH/NTO bipropellant engine for apogee boost maneuvers: AIAA99-2466 [R]. USA: AIAA, 1999.[3] WU P K. Qualification testing of 2nd generation high performance apogee thruster: AIAA 2001-3253 [R]. USA: AIAA, 2001.
[4] HENDERSON S, STECHMAN C. Performance results for the advanced materials bipropellant rocket(AMBR)engine: AIAA 2010-6883 [R]. USA: AIAA, 2010.
[5] 刘昌国, 张中光, 韩宏印, 汪允武, 孙得川. 高比冲双组元液体远地点火箭发动机研究. 上海航天,2003(4):30-33.
[6] 周红玲, 姜文龙, 刘昌国.国内外卫星用液体远地点发动机发展综述[J].火箭推进,2011,37(5):1-8.
ZHOU Hongling, JIANG Wenlong, LIU Changguo. Development of liquid apogee engine for satellite at home and abroad [J]. Journal of rocket propulsion, 2011, 37(5): 1-8.
[7] 姜文龙,杨成虎,林庆国.高性能卫星用490 N轨控发动机研究进展[J].火箭推进,2011,37(6):9-13.
JIANG Wenlong, YANG Chenghu, LIN Qingguo. Development of high performance 490 N apogee engine for satellites [J]. Journal of rocket propulsion, 2011,37(6): 9-13.
[8] 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(4):1-7.
YANG Chenghu, LIN QINGguo, LIU Changguo. Technology development of high-performance liquid apogee engine [J]. Journal of rocket propulsion, 2013, 39(4): 1-7.
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备注/Memo
收稿日期:2017-09-13; 修回日期:2017-11-30 基金项目: 总装十三五预研课题(30508040301) 作者简介: 赵 婷(1984—),女,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