脉冲爆震火箭发动机高频实验研究

Experiments on high frequency pulse detonation rocket engine

为了研究脉冲爆震发动机的高频工作特性,以航空煤油和压缩氧气为推进剂,采用爆震增强装置,增大推进剂供给压力以及增大电磁阀控制气压力等措施,在脉冲爆震火箭发动机模型上进行了实验,成功获得45Hz时的爆震压力波形。实验结果表明,频率增高,爆震波峰值压力下降,有利于加速缓燃向爆震的转变(Defla-gration to Detonation Transition,DDT)。当爆震充分发展时,爆震波波速基本不变,峰值压力上升时间趋于定值。工作频率为45 Hz时,爆震波峰值的压力为3.2 MPa,爆震波的波速为1 715.5m/s。

In order to study the high frequency pulse detonation rocket engine performance characteristics,aviation kerosene and compressed oxygen were chosen as propellants.A series of measurments were taken to improve the frequency,such as by increasing the propellants supply pressure and valve control pressure.Experiments were conducted on the pulse detonation rocket engine model and a maximum operation frequency of 45 Hz was realized.Experimental results show that the increasing of operation frequency benefits for deflagration to detonation transition while the detonation peak pressure reduces.When the detonation was well developed,both the velocity and the peak pressure tended to be fixed values.When PDRE worked at frequency of 45 Hz,the peak pressure was of 3.2 MPa and the velocity was of 1 715.5 m/s.