某型飞机前起落架噪声特性研究  

Research on Noise Characteristics for a Nose Landing Gear

作　　者：刘兴强[1] 黄文超[1] 李红丽[1] 

机构地区：[1]中国飞机强度研究所,陕西西安710065

出　　处：《西北工业大学学报》2016年第3期456-459,共4页Journal of Northwestern Polytechnical University

基　　金：航空科学基金(20121223006)资助

摘　　要：采用仿真与试验的手段对不同来流速度下某型飞机前起落架1/6缩比模型的噪声特性进行了研究。仿真基于"CFD+CAA"混合方法,气动噪声试验在声学风洞中进行。计算与试验结果的对比表明:特征平面的流场分布十分吻合,起落架下游产生大量的涡结构;低频噪声源位于机轮后缘附近,中高频噪声位于减振支柱与防摆支架之间;起落架噪声频谱呈现为宽频特性,计算结果与试验结果基本吻合;远场噪声呈现为典型的偶极子指向性,偶极子长轴与轮轴方向平行。Experiment and simulation are launched to study the aeroacoustic characteristics of a 1 /6 scale aircraft nose landing gear in this paper. Simulation is based on the ＂ CFD ＋CAA＂ hybrid method. And the flow and noise field is measured in an aeroacoustic wind tunnel. Comparing the results of the simulation with experiments indicate that,the flow field of the simulation agree with the experiment well. Low frequency noise source located around the wheels,and the middle and high frequency noise sources appear between the shock strut and Anti-twist bracket.The sound pressure spectrum curves are almost consistent in low and middle frequency range,and the spectrum of the far field noise is broadband,the dipole and monopole dominate the landing gear noise,and the directivity has a form of dipole.

关 键 词：气动噪声 起落架 气动噪声试验 Mhring声类比法 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]