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为研究一种高频脉冲爆震火箭发动机(Pulse Detonation Rocket Engine,简称PDRE)的排气及推力特性,开展了相关实验和数值模拟研究。利用高速摄影拍摄了PDRE高频工作下的排气阴影图和尾焰图。构建了PDRE单次工作过程的数值模型,得到了发动机的排气过程和推力特性。结果表明:PDRE在靠近出口端点火,形成向封闭端传播的爆震波。回爆波向出口传播,形成第一次排气;在封闭端反射的压力波传出爆震管,形成第二次排气;两次排气贡献的冲量大小相近。
In order to study the exhaust and thrust characteristics of a high-frequency pulse detonation rocket engine (PDRE), relevant experiments and numerical simulations were carried out. The use of high-speed photography took the PDRE high-frequency work under the shadow of exhaust shadow and tail flame. The numerical model of PDRE single working process was constructed, and the exhaust process and thrust characteristics of the engine were obtained. The results show that the PDRE ignites near the exit end and forms a detonation wave that propagates toward the closed end. The return wave propagates to the outlet to form the first exhaust gas. The pressure wave reflected at the closed end propagates the detonation tube to form the second exhaust gas. The impulse contribution of the two exhaust gases is similar in magnitude.