Abstract: Gas dynamic resonance ignition technique was used in design of hydrogen/oxygen small thrust rocket engine. By means of analysis of special impulse and combustion gas temperature in different mixture rate,system parameters of hydrogen/oxygen small thrust rocket engine were determined. Ignition tests of gas dynamic resonance igniter,hot firing tests of hydrogen/oxygen small thrust rocket engine and impulse ignition tests were carried out in different thrust operation conditions. It can be confirmed from the hot firing tests that hydrogen/oxygen small thrust rocket engine can realized multi-restart and stable performance. This may verify the reliability and feasibility of the hydrogen/oxygen small thrust rocket engine.

Key words: Liquid propellant rocket engine;Thruster;Gas dynamic resonance+;Ignition

摘要： 将气动谐振点火技术应用于小推力氢氧火箭发动机的设计,通过分析不同混合比下的比冲和燃气温度,确定了氢氧小发动机的总体参数,开展了在不同工况下点火器的单独试验,氢氧小发动机的全系统试验以及小发动机脉冲起动试验。研究结果表明,氢氧小发动机可以实现多次重复起动,结构完好,性能稳定,验证了应用气动谐振点火技术氢氧小发动机的可靠性及方案的可行性。

关键词: 液体推进剂火箭发动机;推力器;气动谐振+;点火