| 未来大推力氢氧发动机方案初步探讨 |
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| 引用本文： | 郑大勇,张卫红,石文靓.未来大推力氢氧发动机方案初步探讨[J].导弹与航天运载技术,2012(1):1-6. |
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| 作者姓名： | 郑大勇 张卫红 石文靓 |
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| 作者单位： | 北京航天动力研究所,北京,100076 |
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| 摘 要： | 针对未来运载器对动力系统的需求,提出中国下一代大推力氢氧发动机的发展设想,对发动机系统方案、性能参数、动态特性和可靠性等方面进行了初步设计和分析比较。结果表明,所选择的发动机系统方案的可靠性、经济性和系统性能符合未来大推力氢氧发动机的技术发展趋势。
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| 关 键 词： | 氢氧火箭发动机 重型运载火箭 系统方案设计 |
Fundamental Research on System Scheme of Next-generation High Thrust LOX/LH2 Rocket Engine |
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| Zheng Dayong
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Zhang Weihong
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Shi Wenliang.Fundamental Research on System Scheme of Next-generation High Thrust LOX/LH2 Rocket Engine[J].Missiles and Space Vehicles,2012(1):1-6. |
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| Authors: | Zheng Dayong Zhang Weihong Shi Wenliang |
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| Affiliation: | (Beijing Aerospace Propulsion Institute,Beijing,100076) |
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| Abstract: | Aiming at current requirement of engine for the next-generation launch vehicle,suggestion of developing a new high thrust LOX/LH2 rocket engine is brought forward,and the fundamental research on power cycle,engine performance,transient character and reliability are conducted.The result indicates that the engine with high reliability,low production cost and appropriate performance is in accordance with the technical trend of future cryogenic LOX/LH2 engine. |
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| Keywords: | LOX/LH2 rocket engine Heavy-lift launch vehic1e System design |
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