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首页> 外文期刊>Chinese journal of aeronautics >Experimental Investigation on Performance of Pulse Detonation Rocket Engine Model
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Experimental Investigation on Performance of Pulse Detonation Rocket Engine Model

机译：脉冲爆震火箭发动机模型性能的实验研究

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The PDRE test model used in these experiments utilized kerosene as the fuel, oxygen as oxidizer, and nitrogen as purge gas. The solenoid valves were employed to control intermittent supplies of kerosene, oxygen and purge gas. PDRE test model was 50 mm in inner diameter by 1.2 m long. The DDT (deflagration to detonation transition) enhancement device Shchelkin spiral was used in the test model. The effects of detonation frequency on its time-averaged thrust and specific impulse were experimentally investigated. The obtained results showes that the time-averaged thrust of PDRE test model was approximately proportional to the detonation frequency. For the detonation frequency 20 Hz, the time-averaged thrust was around 107 N, and the specific impulse was around 125 s. The nozzle experiments were conducted using PDRE test model with three traditional nozzles. The experimental results obtained demonstrated that all of those nozzles could augment the thrust and specific impulse. Among those three nozzles, the convergent nozzle had the largest increased augmentation, which was approximately 18%, under the specific condition of the experiment.
机译：这些实验中使用的PDRE测试模型使用煤油作为燃料，使用氧气作为氧化剂，使用氮气作为吹扫气体。电磁阀用于控制煤油，氧气和吹扫气体的间歇供应。 PDRE测试模型的内径为50毫米，长为1.2 m。在测试模型中使用了DDT（爆燃到爆轰过渡）增强装置Shchelkin螺旋。实验研究了爆轰频率对其时均推力和比冲的影响。所得结果表明，PDRE试验模型的时均推力与爆轰频率大致成正比。对于20 Hz的爆震频率，时间平均推力约为107 N，比脉冲约为125 s。使用带有三个传统喷嘴的PDRE测试模型进行了喷嘴实验。获得的实验结果表明，所有这些喷嘴都可以增加推力和比冲。在这三个喷嘴中，在实验的特定条件下，会聚喷嘴的增幅最大，约为18％。

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