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

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