飞机起落架气动噪声试验  

Noise Experiment for an Aircraft Landing Gear

作　　者：延浩 黄文超[1] 刘兴强[1] 宁方立[2] 

机构地区：[1]中国飞机强度研究所,西安710065 [2]西北工业大学,西安710000

出　　处：《科学技术与工程》2016年第19期116-120,共5页Science Technology and Engineering

基　　金：航空科学基金(20121223006)资助

摘　　要：针对某型飞机前起落架1/6缩比模型及起落架支柱在声学风洞中进行了气动噪声试验研究。试验结果表明:起落架与起落架支柱噪声具有宽频噪声特性;噪声源主要是偶极子和单极子声源,远场噪声具有一定的偶极子指向性;噪声频谱出现明显的峰值噪声,其频率随流速的增大而增加,这是减振支柱与防扭臂的干涉噪声;噪声频率与起落架结构的特征尺寸长度相关,尺寸较大的结构引起中低频噪声,尺寸较小的结构引起高频噪声。Noise experiment is launched for a 1/6 scale nose landing gear and its＇ components in the wind tunnel to study the mechanism of noise generation and the noise characteristic.The test results show that the spectrum of the far field noise is broadband,the dipole and monopole dominate the landing gear noise,and directivity has a form of dipole.The interaction noise between damping pillar and torque link is tonal,and the frequency of this noise is incrased along with the wind speed.The noise frequence is related to the characteristic length of the landing gear parts.Low frequency noise is induced by the wheels,and mid-high frequency noise is damping pillar and torque link.The conclusion of this experiment gives service to the low noise landing gear design.

关 键 词：起落架噪声 气动噪声试验 传声器阵列 声学风洞 

分 类 号：V216.54[航空宇航科学与技术—航空宇航推进理论与工程]