| 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,应当采用氢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。 |
| 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 |
| DOI： |
| 分类号:V434 |
| 基金项目:国家“八六三”基金资助项目 (863 2 3 4 8) |
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| Design and comparison of tripropellant liquid rocket engine system scheme |
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TAN Jian-guo, WANG Zhen-guo
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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. |
| Key words: Liquid propellant rocket engine Tripropellant System performance Parameterization |
