小推力气/液非自燃火箭发动机喷注器

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小推力气/液非自燃火箭发动机喷注器

本发明公开了一种应用于航天器姿态控制发动机的小推力气/液非自燃火箭发动

机喷注器，包括喷注器架( 2 )，其内部设置有火花塞( 1 )、同轴连接的内喷嘴( 6 )和外喷嘴( 7 )；内喷嘴( 6 )的喷口缩进外喷嘴( 7 )喷口；火花塞( 1 )的出口处设置有点火自击单元( 21 )；火花塞( 1 )的外缘环缝设置有同气态组元通道( 10 )连接的点火环缝喷口( 11 )；内喷嘴( 6 )与气态组元通道( 10 )相连通；外喷嘴( 7 )通过切向孔( 22 )同液态组元通道( 20 )相连通；外喷嘴( 7 )的外缘设置有冷却环槽( 24 )。本发明解决了发动机可靠点火及冷却的问题；取得了小推力气/液非自燃火箭发动机稳态/脉冲双工作模式的有益效果。

Low-thrust gas/liquid non-autoignition rocket engineinjector

The invention discloses a low-thrust gas/liquid non-autoignitionrocket engine injector applied to a spacecraft posture control engine. Thelow-thrust gas/liquid non-autoignition rocket engine injector comprises an injectorframe (2), the injector frame (2) is internally provided with a spark plug (1),an inner nozzle (6) and an outer nozzle (7), wherein the inner nozzle (6) andthe outer nozzle (7) are coaxially connected; a spraying opening of the innernozzle (6) is retracted into a spraying opening of the outer nozzle (7); an outletof the spark plug (1) is provided with an ignition self-impact unit (21); a circumferentialweld in the outer edge of the spark plug (1) is provided with an ignition circumferentialweld spraying opening (11) connected with a gas-state component channel (10);the inner nozzle (6) communicates with the gas-state component channel (10);the outer nozzle (7) communicates with a liquid-state component channel (20)through a tangential hole (22); and the outer edge of the outer nozzle (7) isprovided with a cooling circular groove (24). According to the low-thrust gas/liquidnon-autoignition rocket engine injector, the problems of reliable ignition andcooling of the engine are solved; and the beneficial effect of steady-state/pulsedual working modes of a low-thrust gas/liquid non-autoignition rocket engine isachieved.