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发动机燃气射流产生的起始冲击波对于承载体具有破坏作用 ,必须采取抑制措施减弱其影响。多孔抑制器就是采用抑制措施之一。该文对具有不同开孔率的起始冲击波抑制器的抑制效率进行了对比实验研究。实验中采用了实验发动机 ,并且测量了燃气射流所产生的起始冲击波在弧面刚性斜板上的反射压力。通过基于子波的分析方法 ,对压力数据进行了分析 ,获得了基于子波系数的频带能量谱和冲击波强度指数。提出了评估抑制器抑制效率的 2种抑制效率 ,即峰值抑制效率和强度指数抑制效率。研究结果表明 ,抑制器对火箭导弹发射流场的起始冲击波有抑制作用 ,开孔率较小时在近场有较好的抑制效果
The initial shock wave produced by the engine gas jet has a damaging effect on the carrier and must be restrained to reduce its impact. Porous suppressor is one of the inhibition measures. In this paper, comparative experiments on the suppression efficiency of initial blast suppressors with different opening rates were carried out. The experimental engine was used in the experiment, and the reflection pressure of the initial shock wave generated by the gas jet on the curved ramp was measured. Based on the wavelet analysis method, the pressure data are analyzed, and the energy spectrum of the frequency band and the shock wave intensity index based on the wavelet coefficients are obtained. Two kinds of inhibition efficiencies, namely, peak suppression efficiency and intensity index suppression efficiency, were evaluated to evaluate suppressor suppression efficiency. The results show that the suppressor has an inhibitory effect on the initial shock wave of the rocket missile launch flow field, and has better suppression effect in the near field when the opening ratio is small