简述了脉冲爆震火箭发动机的实验系统，利用电磁阀控制煤油，氧气和隔离气体，避免了连续燃烧。
A prototype of pulse detonation rocket engine (PDRE) is introduced to solenoid valves for the control of oxygen, kerosene and isolation gas; thus continuous combustion is avoided.
在发动机控制系统中，电控点火装置对发动机的点火控制包括点火提前角控制、通电时间控制和爆震控制3个方面。
In the control system of engine, the control of electronic control ignition equipment to the engine ignition consists of the following 3 parts: advanced ignition Angle, conduction time and detonation.
所以对于脉冲爆震爆震发动机应采用调节爆震频率和燃气填充相结合的控制策略。
Therefore, a cooperation method of the frequency and fuel flow should be used for pulse detonation engine control.
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