A prototype of pulse detonation rocketengine (PDRE) is introduced to solenoid valves for the control of oxygen, kerosene and isolation gas; thus continuous combustion is avoided.
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。
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A pulse detonation rocketengine (PDRE) is a new propulsion system that generates thrust by using high-temperature and high-pressure air produced by pulse detonation waves.