氢氧谐振点火器多室同步点火研究  

Research on synchronistic multi-ignitions of hydrogen-oxygen resonance ignitor

作　　者：俞南嘉[1] 张国舟[1] 宋雅娜[1] 程圣清 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]北京航天动力研究所,北京100074

出　　处：《北京航空航天大学学报》2005年第6期627-631,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：将气动谐振点火技术应用于塞式喷管发动机多推力室的多次同步点火,研制了新型的氢氧谐振点火器.通过对点火器的点火响应时间、点火延迟时间、多次点火的重复性以及点火器寿命等方面进行试验研究,验证了新研制的点火器具有起动快、点火延迟时间短、多次点火重复性好、寿命长等特点.采用2个点火器联试的方式进行了5次同步点火试验,研究了连接管路对同步性的影响,并提出了进一步缩短同步性时差的方法,结果表明氢氧谐振点火器完全可以满足塞式喷管发动机多推力室同步点火的要求.New hydrogen-oxygen resonance igniter is designed to use in synchronistic multi-ignition for aero-spike nozzle engine. Ignition start time, delay time, repetition of multi-ignition and lifetime of igniter are tested. It can be found from performance tests that the new hydrogen-oxygen resonance igniter with quick starting, short time delay for ignition, good repetition and long life time. Two igniters are used in every synchronistic ignition tests. The pipeline s influence to synchronization is analyzed. Two ways are put forward for shorten the time difference of synchronistic. It can be concluded from total 5 times synchronistic ignition tests that the new hydrogen-oxygen resonance igniter can satisfy the requirements of synchronistic multi-ignition for aerospike nozzle engine and other liquid propellant rocket engines which need synchronistic multi-ignition.

关 键 词：谐振 点火 同步 液体推进剂 火箭发动机 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]