三组元液体火箭发动机系统方案设计与比较

推进技术 ›› 2003, Vol. 24 ›› Issue (5): 406-409.

三组元液体火箭发动机系统方案设计与比较

谭建国,王振国

国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073

发布日期:2021-08-15
基金资助:
国家“八六三”基金资助项目 (863 2 3 4 8)

Design and comparison of tripropellant liquid rocket engine system scheme

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

Published:2021-08-15

摘要/Abstract

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

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

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.