Abstract: An coaxial variable area injector used in the hypergolic bipropellant variable thrust liquid rocket engines is investigated.The propellant components are mixed and two cone stream and then splash on a sphere. The good compatibility between the injector and the ablation cooling chamber has been proved by the test results of more than one hundred thousand seconds burning test time. Thrust ratio may reach 5:1. The combustion effeciency ηc* can reach as high as 0.95 with L* = 0.5 m and εc = 5. It is also proved that the injector has the function of relighting and impulsing.

Key words: Rocket propellant injector;Controllable thrust engine;Liquid propellant rocket engine;Design;Test

摘要： 本文介绍一种同轴环形可变截面喷注器,它用于双组元自燃推进剂变推力液体火箭发动机中,采用环形液流撞击-溅击进行组元的混合和雾化.经过万余秒的热试验证明该喷注器与高硅氧酚醛树脂材料的烧蚀推力室具有良好的相容性;推力变比可达5:1;与L=0.5m的燃烧室匹配,高推力下的燃烧室效率可达95%;该喷注器还具有重复起动或脉冲工作的能力.

关键词: 火箭推进剂喷嘴;可调推力火箭发动机;液体推进剂火箭发动机;设计;试验