某型飞机前起落架结构件气动噪声试验  

Noise experiment of an aircraft's landing gear structure

作　　者：薛彩军[1] 许远[1] 龙双丽[1,2] 聂宏[1] 

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点学科实验室,江苏南京210016 [2]School of Engineering Science,University of Southampton,Southampton SO17 1BJ,UK

出　　处：《空气动力学学报》2012年第3期307-311,共5页Acta Aerodynamica Sinica

基　　金：航空科学基金(2009ZA52001);江苏省普通高校研究生科研创新计划资助项目(CX10B_105Z;CX10B_088Z);南京航空航天大学研究生创新基地(实验室)开放基金资助项目

摘　　要：以某型飞机前起落架为研究对象,通过气动声学风洞试验研究缓冲支柱及扭力臂组合件的气动噪声产生机制、声源特性和影响因素。根据所得数据绘制了噪声频谱特性曲线。通过改变扭力臂的位置,分析了扭力臂对起落架噪声的影响。试验结果表明:缓冲支柱及扭力臂结构件的气动噪声包含钝体绕流噪声和干扰噪声,主要噪声源为偶极子声源,且噪声场具有一定的指向性;扭力臂在缓冲支柱后时总声压级低于扭力臂在前时的总声压级。试验结果可作为起落架低噪声结构优化设计的基础。Taking an aircraft＇s nose landing gear as a test model, the noise generation mechanisms, noise characteristics and influence factors are investigated in the wind tunnel, where the noise frequency spectra are measured. The influence of torque link is analyzed by modifying its position. The test results show that the noise of the assembly of buffer pillar and torque link including bluff body noise and interaction noise. The main noise source has a directivity of a form of the dipole. The overall sound pressure level （OASPL） is low- er for the case with the torque link downstream to the buffer pillar than that of the case with an upstream torque link. The finding can be helpful for the optimization of a landing gear design from the perspective of noise.

关 键 词：声学测量 声学风洞 起落架 扭力臂 气动噪声 

分 类 号：V217[航空宇航科学与技术—航空宇航推进理论与工程]