摘要
对某型飞机主起落架结构件的气动噪声特性进行了声学风洞试验和数值仿真分析。在声学风洞中，借助麦克风测量获得不同来流速度下噪声频谱特性。采用分离涡方法仿真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，利用FW-H方程积分外推法求解声场，分析噪声的频谱特性、远场指向特性及其产生的机制。结果表明：起落架结构件噪声频谱特性仿真结果与试验结果在低频和中频段吻合较好；起落架结构件噪声呈现宽频噪声的特性；频谱曲线以及频谱中优势频率均随着来流速度的增加而增大；仿真曲线中的能量峰值分别对应于缓冲器与支柱、缓冲器与摇臂的干扰噪声；形成此噪声源的压力脉动位于缓冲器下部表面区域；缓冲器和摇臂是总噪声的主要贡献源，支柱对总噪声的贡献量最小；噪声辐射呈现非对称的指向特性。
Abstract
Experimental research and simulation analysis are performed on aeroacoustic noise characteris-tics of an aircraft’s main landing gear component in this paper. The sound field radiated from the model is measured in the aeroacoustic wind tunnel at different wind speeds. The noise spectra are evaluated by the mi-crophones. Detached Eddy Simulation is used to produce the flow field of the model. The source strength and location are determined though the vortex sounds theory. The acoustic field is calculated via FW-H equation. The frequency spectra, the directivity characteristics and the noise mechanism are subsequently studied. The results indicate that the low and the middle spectra from the simulation agree with that from the experiment. The noise radiated from the model is broadband noise. The spectra and dominant frequencies increase with the incensement of the wind speed. In the spectra there are two energy peaks which are corresponding to the inter-action noise between shock absorber and strut, shock absorber and bogie, respectively. The pressure fluctuation which forms the noise sources is on the down surface of the shock absorber. The shock absorber and bogie is main contributor while the strut is the least contributor to the total noise. Noise radiation has dissymmetric directivities.
关键词
起落架 /
气动噪声 /
声学测量 /
噪声预测 /
声类比
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Key words
landing gear /
aerodynamic noise /
acoustic measurement /
noise prediction /
acoustic analogy
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龙双丽;聂宏;薛彩军;许鑫.
某型飞机主起落架结构件气动噪声特性研究[J]. 振动与冲击, 2013, 32(1): 134-139
LONG Shuang-li;NIE Hong;XUE Cai-jun;XU Xin .
Noise characteristics of an aircraft’s landing gear structure[J]. Journal of Vibration and Shock, 2013, 32(1): 134-139
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