民用飞机增升装置气动噪声学风洞试验初步研究  

Preliminarily Investigation on High Lift System Aerodynamic Noise in Wind Tunnel Tests of Civil Aircraft

作　　者：李强[1] 陈迎春[1] 李亚林[1] 张卫民[2] 陈大斌[2] 

机构地区：[1]上海飞机设计研究院,上海201210 [2]中国航天空气动力技术研究院,北京100074

出　　处：《民用飞机设计与研究》2013年第3期6-11,共6页Civil Aircraft Design & Research

摘　　要：采用模拟退火法阵列优化设计技术设计了对数螺旋麦克风阵列,开发了基于"波束成型理论"的阵列试验数据处理软件。将风洞麦克风相阵列噪声识别技术用于SCCH模型增升装置气动噪声研究,开展了增升装置气动噪声源的远场定位探测和强度测量,并用数据处理软件对风洞试验数据进行处理。试验结果表明,随着观察频率的变化缝翼噪声声源的位置与强度会发生变化,襟翼侧缘噪声是一个宽频噪声,不同频率下其强度分布存在差异。同时也发现缝翼安装支架对缝翼和襟翼气动噪声声源有较大影响。文中也给出了多种工况下缝翼和襟翼噪声源分布。An optimal logarithm spiral microphone phrase array was designed by adopting the simulated annealing optimal method, and data processing software was developed based on the Beam Forming theory. The wind tunnel microphone phrase array test technique was employed to study the aerodynamic noise of SCCH high lift system. The far-field detecting and measurement of the noise source were carried out and all test data were processed by using the software. The results show that the location and the pressure level of sound sources for slats varied with the change of inspecting frequency; while the noise source for flap side-edge is a broadband one, and its intensity dis- tribution has differences with different frequencies. Meanwhile, it is found that the slat supporting frames on SCCH test model have significant effects on aerodynamic noise emission. The mapping of noise source for slats/flaps under several test conditions are also presented and analyzed.

关 键 词：声学 增升装置 麦克风相控阵列 风洞试验 气动噪声 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]