三组元液体火箭发动机系统方案设计与比较  

Design and comparison of tripropellant liquid rocket engine system scheme

作　　者：谭建国[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2003年第5期406-409,共4页Journal of Propulsion Technology

基　　金：国家"八六三"基金资助项目 (863 2 3 4 8)

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。Different system schemes of tripropellant liquid rocket engines were designed based on the system equilibrium conditions and the parametric design as well as 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 12.7 MPa; while stage combustion cycle is the best when chamber pressure is higher than 12.7 MPa. This research is the foundation for experimental tripropellant engine work in the next step.

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 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]