航天推进技术研究院主办
[1]曹文庆,谭海林,李伟.低温发动机试验推进剂人口温度控制[J].火箭推进,2009,35(03):52-54.
Cao Wenqing,Tan Hailin,Li Wei.Propellant inlet temperature control for cryogenic rocket engine tests[J].Journal of Rocket Propulsion,2009,35(03):52-54.
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Cao Wenqing,Tan Hailin,Li Wei.Propellant inlet temperature control for cryogenic rocket engine tests[J].Journal of Rocket Propulsion,2009,35(03):52-54.
低温发动机试验推进剂人口温度控制
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
35
期数:
2009年03期
页码:
52-54
栏目:
测控与试验
出版日期:
2009-06-30
- Title:
- Propellant inlet temperature control for cryogenic rocket engine tests
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 阐述了低温发动机起动前推进剂入12温度对试车的重要性。分析了以往试车入 I=I温度过高的原因。通过对试验系统的改造，采用强迫排放推进剂的方法．降低发动机入口 推进剂温度，保证发动机在起动前推进剂入口温度满足试验要求。经试车验证，所采取措施 成功解决了试验系统存在的推进剂入口温度过高的问题。
- Abstract:
- Factors affecting the propellant inlet temperatures during liquid rocket engine tests were analyzed．Methods were adopted for reducing the propellant inlet temperature by modification of the test system and forced dump cooling of the propellant．Tests proved that the improved approaches are effective and the propellant inlet temperature meets the requirement very well．
参考文献/References:
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设计[J]．火箭推进，2008，34(3)：53—57．
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用[J]．火箭推进，2004，30(：1)：35—40．
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天运载技术。2000(5)：37—39．
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备注/Memo
收稿日期：2008--03—25：修回日期：2008-06-16。 作者简介：曹文庆(1980-)，男，工程师，研究领域为发动机试验下艺。
更新日期/Last Update:
1900-01-01