关键词: 双组元推进剂火箭发动机;可调推力火箭发动机;火箭推进剂喷嘴;设计

Abstract: The injector with a pin throttle in liquid bipropellant thrust-variable rocket engines has the superiority of fast response and the disadvantages of high mixture ratio deviation and unreliable shutdown. In this paper, a simple a-nd reliable design of the injector able to overcome the disadvantages mentioned above is presented based on the analysis of its flow characteristics, which is experimentally proved reasonable and reliable.

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