基于可变形空腔的起落架舱体噪声抑制研究

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振动与冲击 ›› 2022, Vol. 41 ›› Issue (3) : 99-106.

论文

基于可变形空腔的起落架舱体噪声抑制研究

翟庆波1，宁方立1，丁辉1，刘哲1，韦娟2，李宝清3

作者信息 +

Noise suppression of landing gear cabin based on deformable cavity

ZHAI Qingbo1, NING Fangli1, DING Hui1, LIU Zhe1, WEI Juan2， LI Baoqing3

Author information +

文章历史 +

摘要

提出了一种基于可变形空腔的起落架舱体结构，通过机械装置调节舱体底板及后壁倾斜角度，不需要额外增加舱体体积，使用声学有限元法探讨了该结构在低马赫数下的噪声抑制效果，研究发现，随着舱体后壁倾斜角度的增大，舱体内部及外部的噪声明显减小，同时模态频率逐渐增大，有助于避免舱体结构发生共振破坏；舱体后壁倾斜一个较小的角度就能有效地改善内部的声反射环境，进而抑制舱体内部的高频模态噪声、总声压级。当后壁倾斜角度大于某个临界值时，继续增大倾斜角度对于舱体内部高频模态噪声以及总声压级的抑制效果不再明显，在当前的仿真条件下，舱体后壁最佳倾斜角度范围为10°到16°。

Abstract

A landing gear cabin structure based on the deformable cavity is proposed. The tilt angles of the cabin floor and rear wall are adjusted by mechanical devices without additional cabin volume. The acoustic finite element method is adopted to investigate the noise suppression effect of the proposed structure at low Mach numbers. It is found that with the increase of the rear wall tilt angle, the noise inside and outside the cabin is significantly reduced. Meanwhile, the modal frequencies gradually increase, which is beneficial to avoid the occurrence of cabin structure. A small rear wall tilt angle can effectively improve the internal sound reflection environment, thereby suppressing the high-frequency modal noise and the overall sound pressure level inside the cabin. When the rear wall tilt angle is greater than a certain critical value, further increasing the tilt angle has no obvious effect on the suppression of high-frequency modal noise and the overall sound pressure level. Under the current simulation conditions, the optimal range of the rear wall tilt angle is from 10 degrees to 16 degrees.

导出引用

翟庆波1，宁方立1，丁辉1，刘哲1，韦娟2，李宝清3. 基于可变形空腔的起落架舱体噪声抑制研究[J]. 振动与冲击, 2022, 41(3): 99-106

ZHAI Qingbo1, NING Fangli1, DING Hui1, LIU Zhe1, WEI Juan2， LI Baoqing3. Noise suppression of landing gear cabin based on deformable cavity[J]. Journal of Vibration and Shock, 2022, 41(3): 99-106

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