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    A kind of shield method for reducing supersonic gas impinging jet noise
    一种超声速气体冲击射流噪声的屏蔽抑制方法
    Experimental Study of Characteristics of Jet Noise Field
    射流噪声场特性的试验研究
    ON THE SAW-TOOTH CHARACTERISTIC AND ITS MECHANISM OF THE IMPINGING JET NOISE FROM SMALL DIAMETER NOZZLE ONTO LARGE FLAT PLATE
    小口径喷嘴冲击射流噪声锯齿特性及机理研究
    Experimental investigation on noise characteristics of jets impinging on concave and convex plates
    凹凸板冲击射流噪声特性的实验研究
    Secondly, the generation process rocket launching noise and its relationship with rocket exhaust has been gained by experimental study of free exhaust. Its formation and developing mechanism is deduced.
    其次,通过对火箭自由射流噪声的实验研究,揭示了火箭发射噪声与燃气射流的关系,并说明了其形成的机理。
    The characteristic of rocket noise is also one of the important factors in integration of rocket system.
    火箭燃气射流噪声特性也是武器系统集成化所考虑的重要因素之一。
    In recent years,research on jet noise has made much headway.
    对不同喷口直径的单股亚音速射流及非设计状态超音速射流噪声场进行了试验研究,获得了射流噪声的总声压场分布特性.
    To deal with the complicated jet noise, wavelet frequency band spectrum and shock wave intensity index is defined on the base of wavelet coefficient.
    针对测试数据中所含有复杂的射流噪声 ,定义了基于小波系数的小波频带能量谱和冲击波的强度指数。
    Wavelet analysis was applied to obtain frequency band energy spectrum of pressure data based on wavelet coefficient. Pressure changing with low frequency was extracted by wavelet filter. The relationship between shock impulse on the cover and amplitude of shock oscillation was also obtained.
    实验测量了对发射管壁静压和密封盖受到的燃气射流冲击压力 ,利用子波分析方法求取了实验数据的基于子波系数的频带能量谱 ,并对含有射流噪声的测量数据进行了子波滤波 ,得到了各点压力低频成分的变化情况 ,同时得到了密封盖所受冲击冲量与激波振荡幅值的关系。
 

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