火箭发动机射流复杂噪声测量数据时频分析  

Time-frequency Analysis of Test Data from Complex Noise of Rocket Engine Jet

作　　者：周帆[1] 姜毅[1] 张学文[1] 郝继光[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《弹箭与制导学报》2012年第3期145-147,151,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了对大推力火箭发射时产生的噪声特性进行预测,采用了小型固体火箭发动机来开展缩比实验研究。通过小波变换和FFT方法对实验测得的噪声数据进行深入分析后发现:在发动机工作时间段出现了低频高幅冲击波成分,其幅值和频率特性与典型射流宽带噪声有很大不同;滤掉该冲击波成分之后的噪声频谱是典型的湍流宽带噪声频谱,并且得到射流噪声的声效率为0.51%,很好的吻合了火箭发射时声效率的经验数据,由此证明该冲击波成分并不属于射流噪声。In order to predict characteristics of high-thrust rocket launching noise, a sub-scale solid engine was chosen for experiment. The wavelet transform and FFT methods were used in processing experimental noise data, the following results can be found out： the low-fre- quency and high-amplitude shock components are found in the engine＇ s working time, and their amplitude and frequency are very different from classic jet broadband noise; The filtered noise spectrum is typical turbulent broadband noise spectrum, and the sound efficiency of jet noise is 0.51% , which is in good agreement with empirical data of rocket launching, so it can be concluded that shock noise is not a part of jet noise.

关 键 词：燃气射流 噪声 小波变换 FFT 冲击波 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]