固体火箭发动机喷流噪声测量及声场分析

Experimental study on jet noise characteristics of solid rocket motor

为了研究分析固体火箭发动机喷流噪声特性及其声场分布规律,设计实验发动机,采用LMS数据采集系统及噪声处理软件通过传感器对固体火箭发动机喷流噪声进行实验采集和测量分析。实验结果表明:同一测量位置处,随着推进剂燃温的降低,噪声峰值降低;随着燃烧室压力及喷管出口马赫数的增高,噪声峰值升高;该实验工况下,发动机喷流噪声声压级分布在120～140dB,峰值频率4500～5000Hz。实验结果对固体火箭发动机喷流噪声场的预测提供了实验依据。

To investigate the characteristics of jet noise for solid rocket motor, the jet is pro- duced by an experimental solid rocket motor. Rocket noise was measured by microphones, and then analyzed by the LMS SCADAS. The experimental results indicate that the sound pressure level peak decreases with increasing propellant temperature, while there is an increase in sound pressure level peak with the increasing chamber pressure and nozzle outlet Mach number. Under this experimental condition, the sound pressure level of solid rocket motor distributed at the bounds of 120-140dB, with a high peak frequency of 4500-5000Hz. Experimental results serve as important reference to prediction of solid rocket noise.