火箭喷气强噪声模拟装置内声场特性分析

The Characteristic Analysis of Interior Aound Field of Rocket Jet Strong Noise Simulation Device

建立了火箭喷气强噪声模拟装置产生单元音圈振膜振速有效值的计算模型、电声转换效率计算模型。喉部声压计算模型以及有导流锥时锥形声辐射段和指数声辐射段出口声压计算模型,运用MATLAB软件对这些模型在不同频率下进行仿真分析。仿真结果表明:与无导流锥相比,有导流锥时声辐射段喉部声压较高;在谐振频率处电声转换效率达到最大值,并且声辐射段出口处的电声转换效率大于喉部;与锥形声辐射段相比,指数声辐射段沿轴线方向面积增加较缓慢,声波在声辐射段中传播时声压衰减较小。

The computing models of the particle velocity of voice coil diaphragms,the electro acoustical efficiency,the throat pressure and the outlet pressure of conical acoustic radiation section and exponential acoustic radiation section with diversion-cone of the rocker jet strong noise simulation unit device have been created. These computing models are simulated under the condition of different frequencies by using MATLAB. The calculated results show that the throat pressure of the acoustic radiation section with diversion-cone is higher than the one that without it; the electro acoustical efficiency reaches its maximum at the resonant frequency,and the efficiency of the outlet is higher than the throat; compared with the conical acoustic radiation section,the area of the exponential acoustic radiation section increase slowly along the axis,and the decline of the sound pressure is minor when the acoustic wave propagation.