爆震波点火器在氢氧塞式喷管的工程应用  

Engineering application of detonation wave igniter on hydrogen-oxygen aerospike nozzle engine

作　　者：郭红杰[1] 梁国柱[1] 马彬[1] 刘宇[1] 信伟[2] 郑孟伟[2] 

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,北京100076

出　　处：《火箭推进》2006年第6期16-19,共4页Journal of Rocket Propulsion

摘　　要：建立了氢氧爆震波点火器试验系统,并根据试验塞式喷管发动机工作状态要求设计了爆震波点火器。在高空条件下(0.005￣0.002MPa),爆震波点火器供气压力0.3MPa、混合比3左右,对爆震波点火器的点火性能进行了试验,成功实现了高空条件下爆震波点火火炬。在同样高空条件下对爆震波点火器点燃单元塞式喷管试验发动机成功进行了点火试验。试验结果表明,氢氧爆震波点火器能以较低的供气压力实现可靠点火。爆震波点火器在气氢气氧单元塞式喷管试验发动机点火的成功应用,为下一阶段应用于多管塞式喷管发动机的实际点火试验提供了技术基础。Experiment of the testing system of hydrogen-oxygen detonation wave igniter was performed. To investigate the ignition capability on high altitude of the detonation wave igniter designed for the test requirement, ignition experiments were conducted at 2000Pa-5000Pa in a gas environment, and ignition torch was created succesfully. With the same pressure of environment gas the detonation wave igniter ignited the single combustion chamber aerospike nozzle engine. The results found the technique base of the application of the detonation wave igniter to multi-chamber aerospike nozzle engine.

关 键 词：液体火箭发动机 爆震波 点火器 塞式喷管 

分 类 号：V432[航空宇航科学与技术—航空宇航推进理论与工程]