飞机起落架气动噪声特性仿真与试验

流体力学与飞行力学

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飞机起落架气动噪声特性仿真与试验

龙双丽, 聂宏, 薛彩军, 许鑫

南京航空航天大学航空宇航学院, 江苏南京 210016

收稿日期:2011-08-13 修回日期:2011-09-24 出版日期:2012-06-25 发布日期:2012-06-26
通讯作者: 聂宏 E-mail:hnie@nuaa.edu.cn
基金资助:
江苏省普通高校研究生科研创新计划(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;国家留学基金委资助项目

Simulation and Experiment on Aeroacoustic Noise Characteristics of Aircraft Landing Gear

LONG Shuangli, NIE Hong, XUE Caijun, XU Xin

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2011-08-13 Revised:2011-09-24 Online:2012-06-25 Published:2012-06-26
Supported by:
The Innovative Project for Postgraduate Cultivation of Jiangsu Province (CX10B_105Z, CX10B_088Z); Foundation of Graduate Innovation Center in NUAA; Financial Support from the Program of China Scholarship Council

摘要/Abstract

摘要： 对某型飞机前起落架的气动噪声特性进行了数值仿真分析和声学风洞试验研究。在典型飞机着陆速度下,采用分离涡(DES)方法模拟起落架周围非定常湍流流场,通过涡声理论计算声源的强度和位置,并利用FW-H(Ffowcs-Williams/Hawkings)方程积分外推法求解出不同部件及其组合件产生的声场,分析其噪声的产生机制、频谱特性及远场指向特性,同时评估各部件对总噪声的贡献量。在声学风洞中对轮胎和轮叉组合件进行气动声学试验,借助麦克风测量获得了噪声的频谱特性。基于部件固体表面积分计算的仿真结果与试验结果在声学远场条件下吻合较好。仿真结果表明:起落架气动噪声是钝体绕流噪声和空腔噪声的叠加,呈现宽频噪声的特性。强度最大的声源主要分布在起落架各部件的固体表面;轮胎噪声对总噪声的贡献最大,其次是轮叉噪声,支柱噪声对总噪声贡献最小。各部件噪声和总噪声均具有偶极子声源的辐射特性。空间可穿透积分面计算的声压级结果比固体表面计算的声压级结果大5 dB左右。该研究结果为低噪声起落架设计提供了一定的参考。

关键词: 起落架噪声, 声学测量, 计算气动声学, 涡声理论, 声类比

Abstract: Simulation analysis and experimental research are performed on the aeroacoustic noise characteristics of an aircraft nose landing gear in this paper. At the flight speed during the approach phase, the flow field of an aircraft nose landing gear is produced by means of detached eddy simulation(DES). The source strength and location are determined though the vortex sound theory. Meanwhile, the acoustic field radiated from different model parts or assembled parts are calculated via FW-H(Flowcs-Williams/Hawkings) equation. The noise mechanism, frequency spectra and the directivity characteristics are subsequently studied, and the contribution of each part is assessed. The acoustic field radiated from the assembled parts of the wheel and bogie is measured in an aeroacoustic wind tunnel. The noise spectra are evaluated by microphones. A comparison shows that the simulation results agree well with the experiment results under the acoustic far field condition. The results indicate that the landing gear noise is broadband noise, which is mainly generated by flow separation off the bluff body and superimposed by tonal noise. The sources with the biggest strength are on the solid surface of each part. The wheel is the largest contributor and the strut is the least contributor to the landing gear noise. The noise radiation directivities of each part and the whole model are similar in possessing dipole characteristics. The sound pressure level calculated from the porous surface is about 5 dB greater than that calculated from the solid surface. The results can provide some reference for low noise landing gear design.

Key words: landing gear noise, acoustic measurement, computational aeroacoustics, vortex sound theory, acoustic analogy

中图分类号:

V211.7

龙双丽, 聂宏, 薛彩军, 许鑫. 飞机起落架气动噪声特性仿真与试验[J]. 航空学报, 2012, (6): 1002-1013.

LONG Shuangli, NIE Hong, XUE Caijun, XU Xin. Simulation and Experiment on Aeroacoustic Noise Characteristics of Aircraft Landing Gear[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, (6): 1002-1013.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

飞机起落架气动噪声特性仿真与试验

Simulation and Experiment on Aeroacoustic Noise Characteristics of Aircraft Landing Gear

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