基于大型声学风洞的飞行器起落架噪声实验研究

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振动与冲击 ›› 2022, Vol. 41 ›› Issue (22) : 160-172.

论文

赵鲲1，梁俊彪1，Kopiev Victor2 ，Belyaev Ivan2

作者信息 +

Experimental study on the aircraft landing gear noise in a large-scale aeroacoustic wind tunnel

ZHAO Kun1,LIANG Junbiao1,Kopiev Victor2,Belyaev Ivan2

Author information +

文章历史 +

摘要

起落架是飞行器机体噪声的主要声源，是当前气动声学界关注的一个焦点。为分析不同结构参数对起落架噪声特征的影响，在FL-17 5.5米×4米航空声学风洞开展了大尺度起落架简化模型实验研究。实验包括34m/s～75 m/s范围内五个风速，采用自由场传声器与相位传声器阵列开展声学测量。实验系统分析了模型噪声源位置、部件贡献与噪声指向性规律，获得了风速变化下起落架噪声特征；通过控制结构参数，结果表明起落架高度、轮直径、攻角、轮数、轮攻角对起落架噪声特征具有重要影响，而8o范围内偏角影响相对较弱。
关键词：起落架噪声；大型声学风洞；CLEAN-SC；声源区域积分；国际合作

Abstract

Landing gear is a main source of the airframe noise, which is currently a focus of the aeroacoustic field. In order to study effects on the acoustic performance of the landing gear from different structure parameters, large-scale simplified landing gear model experiment was conducted in the 5.5m×4m aeroacoustic wind tunnel. In the experiment, five velocities were chosen in the range of 34m/s~75m/s. Acoustic measurement was carried out with free field microphones and a phase microphone array. The noise source location, component contribution and noise directivity of the model were analyzed, and the characteristics of landing gear noise under different wind speed were obtained. By controlling the structural parameters, the results show that landing gear height, wheel diameter, angle of attack, wheel number and wheel angle of attack make important effects on the characteristics of landing gear noise, while the effect of deflection angle within 8° is relatively weak.
Key words: landing gear noise; large-scale aeroacoustic wind tunnel; CLEAN-SC; source region integration; international collaboration

导出引用

赵鲲1，梁俊彪1，Kopiev Victor2,Belyaev Ivan2. 基于大型声学风洞的飞行器起落架噪声实验研究[J]. 振动与冲击, 2022, 41(22): 160-172

ZHAO Kun1,LIANG Junbiao1,Kopiev Victor2,Belyaev Ivan2. Experimental study on the aircraft landing gear noise in a large-scale aeroacoustic wind tunnel[J]. Journal of Vibration and Shock, 2022, 41(22): 160-172

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