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。
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).
点火阶段对撞击起爆过程起决定性作用，影响点火阶段的因素就是决定其撞击感度高低的关键因素。
Ignition plays a determinant role in the impact detonation, and the factors that influence ignition are also the crucial ones that decide the impact sensitivity.
另外还对点火增长模型中的不同参数进行调整，定性地测定参数对冲击波起爆性能的影响。
In addition, the different parameters in Ignition and Growth model are adjusted in order to qualitatively examine the influence on shock initiation behavior made by the parameters.
通过采用提高煤油温度及对爆震管壁面加热的方法，对于点火及爆震起爆过程起着十分重要的促进作用。
By means of heating kerosene and the tube wall, the ignition and the subsequent detonation initiation were promoted markedly.
针对两相无阀脉冲爆震发动机（PDE），研究了点火能量、工作频率、发动机直径、进气方式和燃料种类等对PDE点火-起爆性能的影响。
The ignition-detonation performance of two-phase valveless pulse detonation engines(PDEs) with the inner diameters of 50 mm and 120 mm in different operation cases was investigated.
针对两相无阀脉冲爆震发动机（PDE），研究了点火能量、工作频率、发动机直径、进气方式和燃料种类等对PDE点火-起爆性能的影响。
The ignition-detonation performance of two-phase valveless pulse detonation engines(PDEs) with the inner diameters of 50 mm and 120 mm in different operation cases was investigated.
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