摘要
三组元火箭发动机是近几年提出的新概念.本文介绍了三组元推进剂燃烧试验及其结果分析.试验用液氧/丙烷/氢做推进剂在9.78MPa燃烧室压力下完成.试验结果表明,三组元推进剂和三组元发动机概念可行.
Tri-propellant rocket engine is a new concept developed in recent years.The combustion tests of LOX/propane/gas hydrogen tri-propellant are conducted with subscale hardware at chamber pressure of 6.78MPa and the results are analyzed in this paper.It is shown that the concept is feasible.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1989年第6期33-37,共5页
Journal of Propulsion Technology
关键词
液体推进剂
火箭发动机
多元推进剂
燃烧试验
Multipropellant,combustion test,Liquid propellant rocket engine, Analyzing
