基于LBM方法的LAGOON起落架噪声预测与降噪方法研究

李蓝天; 张豪; 张绍广; 张宇飞

doi:10.7638/kqdlxxb-2024.0190

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基于LBM方法的LAGOON起落架噪声预测与降噪方法研究

研究论文 | 更新时间：2026-05-28

- 基于LBM方法的LAGOON起落架噪声预测与降噪方法研究
- Noise prediction and reduction methods for LAGOON landing gear based on Lattice Boltzmann method
- 空气动力学学报 2026年44卷第4期页码：65-76
- 作者机构：
  
  1. 北华航天工业学院航空宇航学院,廊坊,065000
  2. 清华大学航天航空学院,北京,100084
- 作者简介：
  
  李蓝天（1996—），女，河南平顶山人，研究方向：飞行器气动声学与控制. E-mail：lltlilantian@163.com
  张宇飞*（1983—），副教授，研究方向：计算流体力学，湍流模拟. E-mail：zhangyufei@tsinghua.edu.cn
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0190
  中图分类号： V211.3
- 纸质出版：2026
- 稿件说明：
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李蓝天, 张豪, 张绍广, 等. 基于LBM方法的LAGOON起落架噪声预测与降噪方法研究[J]. 空气动力学学报, 2026, 44(4): 65−76.

Li Lantian, Zhang Hao, Zhang Shaoguang, et al. Noise prediction and reduction methods for LAGOON landing gear based on Lattice Boltzmann method[J]. 2026, 44(4): 65-76.
李蓝天, 张豪, 张绍广, 等. 基于LBM方法的LAGOON起落架噪声预测与降噪方法研究[J]. 空气动力学学报, 2026, 44(4): 65−76. DOI： 10.7638/kqdlxxb-2024.0190

Li Lantian, Zhang Hao, Zhang Shaoguang, et al. Noise prediction and reduction methods for LAGOON landing gear based on Lattice Boltzmann method[J]. 2026, 44(4): 65-76. DOI： 10.7638/kqdlxxb-2024.0190.

摘要

起落架是民用飞机起降阶段的重要噪声源之一，研究其噪声产生机理及控制方法具有重要意义。本文基于格子玻尔兹曼方法对起落架LAGOON模型的三维非定常流动进行数值模拟，结合FW-H（Ffowcs Williams-Hawkings）方程计算远场噪声。首先研究了网格分辨率对仿真结果的影响，并与风洞试验结果进行对比，验证了数值模拟结果的可靠性；其次分析了起落架噪声的产生机理和频谱特性，对比了不同FW-H积分面对噪声计算结果的影响；最后探索了起落架模型空腔填充的流动控制效果。研究结果表明：采用空间可穿透面作为FW-H积分面比采用固体表面所获得的仿真结果更接近于试验结果；空腔填充可有效抑制空腔共振，从而降低起落架噪声，在远场飞越方向和横侧方向总声压级均降低约3.0 dB。本文系统验证了基于LBM的声学预测流程在起落架气动噪声问题中的适用性，所揭示的声源机理及空腔填充方案的降噪效果可为后续工程实用的低噪声起落架设计提供方法参考与数据支撑。

Abstract

The landing gear is recognized as a significant source of noise during the takeoff and landing phases of civil aircraft operations. Understanding the mechanisms behind its noise generation and exploring effective control methods are crucial for improving overall noise management in aviation. This article presentd a detailed numerical study employing the Lattice Boltzmann Method (LBM) to simulate the three-dimensional unsteady flow around the LAGOON (LAnding Gear nOise database for civil aviation authority validatiON) model of landing gear. The study applied the Ffowcs Williams-Hawkings (FW-H) equation to compute far-field noise levels. Initially

the research investigated the impact of mesh resolution on simulation results by comparing them against wind tunnel data to verify the accuracy of the numerical calculations. Subsequently

the study analyzed the noise generation mechanisms and spectral characteristics

providing a comparative assessment of the effects of different FW-H integration planes on noise predictions. This analysis highlighted the critical role of integration surface selection in ensuring prediction reliability. Furthermore

the research evaluated flow control strategies

specifically examining the noise reduction effect of cavity filling in the landing gear model. The findings indicate that using a penetrable surface as the FW-H integration surface yields closer agreement with experimental measurements compared to a solid surface. Additionally

cavity filling significantly suppresses resonance phenomena

reducing the total sound pressure level by approximately 3.0 dB in both the far-field flyover and sideline directions. This finding suggests a viable approach for aircraft noise reduction design. This study systematically validates the applicability of LBM based prediction framework for landing gear aeroacoustics. The elucidated noise generation mechanisms and the noise reduction effect of the cavity filling scheme provide methodological insights and data support for subsequent engineering-oriented low-noise landing gear design.

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references

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