催化点火气氢气氧推力器试验研究  

Experimental Investigation on Catalytic Hydrogen and Oxygen Thruster

作　　者：林震[1] 王长辉[2] 刘宇[2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]北京航空航天大学,北京100191

出　　处：《推进技术》2012年第6期897-901,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金(50776002)

摘　　要：为探索催化点火气氢气氧推力器的点火规律和相关性能,设计并搭建了1N催化点火气氢气氧推力器试验系统,进行了冷热试试验。试验成功实现了不同工况下的多次催化点火。结果表明:供给氧氢混合比控制在100时,推力器预燃室产生的点火温度为700℃,能够满足燃烧室点火要求;催化剂面积体积比对催化氢氧点火具有决定性影响,采用面积体积比大的催化载体可以实现常温(8℃)下的催化点火;另外,试验中氢氧燃烧产生的高温和试验结束后推力器内残留的液态水也对催化组件提出了一定的耐温性和防水性要求。In order to study the catalytic ignition law of catalytic hydrogen and oxygen thruster, a 1N catalytic thruster and relative experimental system were constructed. A series of tests were conducted. Several catalytic ignition in different working condition was realized. It indicates that when the oxygen and hydrogen mixture ratio is 100, the measured temperature of pre- combustion is 700℃ , which is the most applicable ignition temperature. Catalytic ignition in normal temperature can be real- ized using palladium-carbon as catalyzer which shows the domination of surface-volume ratio for catalytic ignition. In addition, it indicates that the ability of fireproof and waterproof is also the key characteristics of the catalyzer parts for catalytic hydrogen and oxwen thruster.

关 键 词：催化点火 气氢气氧推力器 试验研究 面积体积比 燃烧 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]