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

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