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).
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。
The jet flows from vent holes in a center-core igniter strongly influence the process of ignition in guns.
中心点火管传火孔射流场直接影响火炮膛内的点火传火过程。
According to the different motor ignition states, a series of total pressure values of observed points on the respective jet axis distances was measured.
针对不同的发动机点火状态,在射流轴线的不同距离上对一系列测点位置的总压参数进行了测量。
应用推荐