航天推进技术研究院主办
[1]孙 鑫,杨成虎.5 kN再生冷却发动机推力室传热研究[J].火箭推进,2012,38(02):32-37.
SUN Xin,YANG Cheng-hu.Heat transfer investigation for 5 kN regeneratively-cooled engine thrust chamber[J].Journal of Rocket Propulsion,2012,38(02):32-37.
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SUN Xin,YANG Cheng-hu.Heat transfer investigation for 5 kN regeneratively-cooled engine thrust chamber[J].Journal of Rocket Propulsion,2012,38(02):32-37.
5 kN再生冷却发动机推力室传热研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
38
期数:
2012年02期
页码:
32-37
栏目:
研究与设计
出版日期:
2012-04-15
- Title:
- Heat transfer investigation for 5 kN regeneratively-cooled engine thrust chamber
- 文章编号:
- 1672-9374(2012)02-0032-06
- 分类号:
- V434.14-34
- 文献标志码:
- A
- 摘要:
- 5 kN摇摆发动机推力室采用再生冷却身部，为检验推力室冷却方案设计的合理性，对5 kN再生冷却发动机推力室进行传热计算，分析了再生冷却的影响因素，并针对发动机设计提出了相应的改进措施，改进后的发动机热试车工作正常，表明了改进工作的有效性。
- Abstract:
- 5 kN gimbaled engine adopts the regenerative cooling technology in the thrust chamber design. In order to validate the rationality of the cooling scheme of the thrust chamber, the heat transfer calculation on the regenerative cooling thrust chamber was conducted, and the effects of excess oxidizer coefficient and combustion chamber length on regenerative cooling were analyzed, and an improvement approach for the engine design was put forward. The redesigned engine worked properly in the firing test. It indicates that the improvement approach is effective.
参考文献/References:
[1]刘国球. 液体火箭发动机原理[M]. 北京: 宇航出版社, 1993.
[2]邢继发. 世界导弹与航天发动机大全[M]. 北京: 军事科学出版社, 1999.
[3]徐辉. 10kN双向摇摆再生冷却发动机技术研究[J]. 火箭推进, 2009, 10(5): 8-12.
[4]萨顿G P, 比布拉兹O. 火箭发动机基础[M]. 北京: 科学出版社, 2003.
[5]休泽尔D K. 液体火箭发动机现代工程设计[M]. 北京: 中国宇航出版社, 2004.
[6]杨世铭, 陶文铨. 传热学(第三版). 北京: 高等教育出版社, 2002.
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备注/Memo
收稿日期：2011-11-28；修回日期：2012-02-02
基金项目：国家高技术项目（2006AA702306）
作者简介：孙鑫（1985—），男，硕士，研究领域为空间推进系统设计
更新日期/Last Update:
1900-01-01