中文摘要：

为了实现快速短距起爆,火焰射流点火系统被尝试应用在脉冲爆震火箭发动机上.采用航空煤油为燃料、氧气为氧化剂、压缩氮气为隔离气体,在两相脉冲爆震火箭发动机上成功进行了火焰射流点火起爆实验.利用安装在点火位置后方的多孔孔板来形成火焰射流.实验研究表明,采用火焰射流点火方法,能够在较短距离形成充分发展的两相爆震,在本实验条件下爆燃向爆震转变距离约为管径的4倍.较之爆震管内安装螺旋来促进爆燃向爆震转变的方法,在同一模型机上采用火焰射流点火起爆能够使爆燃向爆震转变的距离缩短60%.

英文摘要：

In order to achieve a rapid initiation of detonation in a short distance, a flame jet ignition system was applied to the pulse detonation rocket engine （PDRE）. Kerosene used as fuel, oxygen as oxidizer and nitrogen as purge gas, the experiment on detonation initiation by a flame jet was successfully conducted on the multi-cycle PDRE. The flame jet was yielded with the aid of a multi-hole orifice plate mounted behind the igniter port. The experimental investigation indicates that a fully-developed two-phase detonation can be achieved in ashort distance by the method of flame jet ignition. In the current experiment, the deflagration-to-detonation transition （DDT） distance obtained was approximately four times of the inner diameter of detonation tube. Compared with the approach of installing Shchelkin spiral in the detonation tube as DDT enhancement device, adopting flame jet ignition on the same PDRE model shortened the DDT distance by 60 % .