| 三组元液体火箭发动机系统方案设计与比较 |
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| 引用本文： | 谭建国,王振国.三组元液体火箭发动机系统方案设计与比较[J].推进技术,2003,24(5):406-409. |
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| 作者姓名： | 谭建国 王振国 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,湖南,长沙,410073 |
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| 基金项目： | 国家“八六三”基金资助项目 (863 2 3 4 8) |
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| 摘 要： | 通过对发动机组件进行参数化设计和分析，利用系统平衡条件，设计出不同方案下的三组元液体火箭发动机。结果表明：当室压低于12．7MPa时，应当采用氧氧富燃燃气发生器循环；高于该值时，应采用分级燃烧循环，为进一步研制三组元液体火箭发动机原理样机奠定了基础。
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| 关 键 词： | 液体推进剂火箭发动机 三元推进剂 系统性能 参数化法 |
| 文章编号： | 1001-4055(2003)05-0406-04 |
| 修稿时间： | 2002年9月23日 |
Design and comparison of tripropellant liquid rocket engine system scheme |
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| TAN Jian-guo and WANG Zhen-guo.Design and comparison of tripropellant liquid rocket engine system scheme[J].Journal of Propulsion Technology,2003,24(5):406-409. |
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| Authors: | TAN Jian-guo and WANG Zhen-guo |
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| Institution: | Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defence Technology, Changsha 410073, China |
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| Abstract: | Different system scheme of tripropellant liquid rocket engines were designed based on the system equilibrium conditions and the parametric design and analysis of engine component. Result shows that hydrogen-oxygen fuel rich gas generator cycle is better than other system scheme when chamber pressure is lower than 12.7MPa; while stage combustion cycle is the best when chamber pressure is higher than 12.7MPa. This research is the foundation for experimental tripropellant engine work in the next step. |
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| Keywords: | Liquid propellant rocket engine Tripropellant System performance Parameterization |
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