火箭推进

液氧/液甲烷姿控发动机点火技术研究

潘一力,周海清,吉林,许宏博

(上海空间推进研究所上海空间发动机工程技术研究中心,上海 201112)

关键词：液氧/液甲烷; 电点火; 激光点火; 姿控发动机

Study on ignition technology of LO_X/LCH₄ attitude control engine

PAN Yili,ZHOU Haiqing,JI Lin,XU Hongbo

(Shanghai Engineering Research Center of Space Engine,Shanghai Institute of Space Propulsion,Shanghai 201112,China)

Keywords：liquid oxygen and liquid methane; electric ignition; laser ignition; attitude control engine

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液氧/液甲烷推进剂组合具有高比冲性能以及其他优异的综合使用性能,已经成为未来空间化学推进的重要发展方向之一。点火技术作为液氧/液甲烷姿控发动机的重大关键技术,对发动机可靠启动、响应特性、脉冲一致性等关键指标具有重要影响。欧美国家已经开展系统以及相关组件的预先研究,其中美国已经完成了系统级的地面自由飞行试验。国内也已开展了低温推进系统技术论证,并开展了主发动机、姿控发动机以及点火器、低温贮箱、低温阀门等关键组件的研发。针对液氧/液甲烷低温推进剂组合进行了点火技术分析筛选和试验研究,验证了电火花点火与激光诱导等离子点火两种方案的原理可行性。试验表明在入口条件从气态到液态的宽广范围内两种方案均能实现可靠、可重复点火,两种点火方式对于LOx/LCH4发动机均原理可行。试验得出可靠点火的火花能量边界特性、混合比边界特性、响应特性以及脉冲特性,为后续液氧甲烷发动机设计提供依据。

In recent years,the propellant combination of liquid oxygen/liquid methane(LOX/LCH4)has become one of the important development directions of space chemical propulsion in the future due to its high specific impulse and excellent comprehensive performance.As a crucial technology of LOX/LCH4 attitude control engine,the ignition technology has an important influence on the starting reliability,response characteristics and impulse consistency of the engine.American and European countries have focused on the system integration and component technologies for the past few years,in which the United States has successfully conducted the system-level free flight test of LOX/LCH4 propulsion system.Technical demonstration of cryogenic propulsion system has been carried out in China,and research and development of main engine,attitude control engine and key components such as igniter,cryogenic tank and cryogenic valve have been conducted.In this paper,the ignition technology of LOX/CH4 attitude control engine was analyzed,screened and tested,and the feasibility of electric spark ignition and laser induced plasma ignition was verified.The experimental results show that both schemes can achieve reliable and repeatable ignition in a wide range of inlet conditions from gaseous phase to liquid phase,which prove that both ignition methods are feasible for LOX/CH4 engine.The boundary characteristics of spark energy,boundary characteristics of mixing ratio,response characteristics and impulse characteristics of reliable ignition are obtained,which provide a basis for the subsequent design of LOX/CH4 rocket engine.

引言
1 液氧/液甲烷点火技术研究概况
2 液氧/液甲烷点火技术方案选择
3 液氧/液甲烷点火技术试验
4 总结与展望

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