Study on Valve Systems for Pulse Detonation Engines
Study on Valve Systems for Pulse Detonation Engines
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DOI：
10.2514/6.2010-6672
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发表时间：
2010-07
期刊：
影响因子：
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通讯作者：
K. Matsuoka;Motoki Esumi;J. Kasahara;Shuji Ogawa
中科院分区：
文献类型：
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作者：
K. Matsuoka;Motoki Esumi;J. Kasahara;Shuji Ogawa
提出了一种新型脉冲爆震火箭发动机旋转阀系统。由于该阀可以通过使用旋转盘将三种气体（氧化剂、燃料、吹扫气体）供应到PDE管（燃烧器）中，因此该阀的重量很轻。为了验证该系统的推力性能，我们利用旋转阀式PDRE系统和乙烯-氧推进剂进行了推力测量。结果，我们确认了系统在很宽的工作频率范围内的稳定运行，并测量了时间平均推力。我们成功地减小了PDRE阀门的尺寸和重量。当工作频率为33.3Hz，推进剂供给压力为1.0MPa时，获得了最大时均推力31.7。当工作频率为33.0Hz、推进剂供给压力为0.7MPa时，发动机的最大比冲为249.5s。
We proposed a novel rotary valve system for a pulse detonation rocket engine (PDRE). Since this valve can supply three gases (oxidizer, fuel, purge gas) into a PDE tube (combustor) by using a rotary disk, the weight of this valve is light. We carried out the thrust measurement by using the PDRE system with the rotary valve and ethylene-oxygen propellant in order to confirm the thrust performance of the system. As a result, we confirmed the stable operation of the system over a wide range of operation frequency and measured the time-averaged thrust. We succeeded reducing the size and the weight of a valve for a PDRE. In addition, the maximum time-averaged thrust of 31.7 was achieved at operation frequency of 33.3 Hz and propellant supply pressure of 1.0 MPa. Moreover, the maximum specific impulse of 249.5 sec was achieved at operation frequency of 33.0 Hz and propellant supply pressure of 0.7 MPa.