小推力火箭发动机

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小推力火箭发动机

本发明公开了一种应用于航天飞行器的小推力火箭发动机，包括燃阀( 1 )、氧阀( 2 )与喷注器( 4 )联接，分别向喷注器( 4 )输送煤油和气态氧；喷注器( 4 )的尾部设置有电点火器( 3 )；喷注器( 4 )与推力室身部本体( 5 )连接；推力室身部本体( 5 )由燃烧室和喷管组成，点火器( 3 )产生的电火花直接点燃喷注器( 4 )喷注面附近的推进剂混气，燃气由喷管排出产生推力。本发明使用气氧/煤油作为推进剂，解决了现有有毒自燃推进剂发动机的环境污染问题，取得了无毒、无污染、高性能、响应快及适应稳态/脉冲双工作模式等有益效果。

Low-thrust rocket engine

The invention discloses a low-thrust rocket engine applied to an aerospacecraft. The low-thrust rocket engine is characterized in that a fuel valve (1)and an oxygen valve (2) are connected with an injector (4) to deliver keroseneand gaseous oxygen to the injector (4) correspondingly; an electric igniter (3)is arranged at the tail of the injector (4); the injector (4) is connected witha thrust chamber body (5); the thrust chamber body (5) is composed of a combustionchamber and a spraying pipe; and electric sparks generated by the igniter (3)directly ignite propellant mixed gas near the injecting face of the injector(4), and fuel gas is exhausted by the spraying pipe to generate thrust. Accordingto the low-thrust rocket engine, the gaseous oxygen/ kerosene are used as a propellant,the problem of environmental pollution of an existing poisonous autoignitionpropellant engine is solved, and the beneficial effects of non-toxicity,non-pollution, high performance, fast response, adaptability to thesteady-state/pulse double working modes, and the like are achieved.