海军航空大学学报2026，Vol.41Issue(3)：473-484,494,13.DOI:10.7682/j.issn.2097-1427.2026.03.006
大尺寸高保真起落架构型气动噪声预测及降噪控制
Aerodynamic Noise Prediction and Noise Reduction Control of Large-Scale High-Fidelity Landing Gear Configuration
李蓝萱 1郑国雨 2董宁娟 3黄江涛 4乔磊 5徐家宽 6白俊强5
作者信息
- 1. 西北工业大学航空学院,陕西 西安 710072||飞行器基础布局全国重点实验室,陕西 西安 710072
- 2. 中国商飞上海飞机设计研究院,上海 201210
- 3. 强度与结构完整性全国重点实验室,陕西 西安 710072
- 4. 中国空气动力研究与发展中心空天技术研究所,四川 绵阳 621000
- 5. 西北工业大学航空学院,陕西 西安 710072||无人飞行器技术全国重点实验室,陕西 西安 710072
- 6. 西北工业大学航空学院,陕西 西安 710072||飞行器基础布局全国重点实验室,陕西 西安 710072||西北工业大学宁波研究院,浙江 宁波 3151032
- 折叠
摘要
Abstract
Numerical simulation of landing gear noise and noise reduction design technologies are of great value and significance for the research and development of civil airliners.This study focuses on large-scale,high-fidelity landing gear configurations with complex geometries,conducting research on broadband aerodynamic noise numerical simula-tion.The prediction accuracy of far-field aerodynamic noise using various turbulence modeling methods,including the improved Delayed Detached Eddy Simulation(IDDES),the Wall-Adapting Local Eddy-Viscosity(WALE)model,and the Dynamic Smagorinsky Model(DSM),is systematically analyzed and evaluated.The results confirm that DSM of-fers the optimal frequency domain resolution for predicting noise in separated flows.Furthermore,the differences in far-field noise calculation using the Ffowcs Williams-Hawkings(FW-H)integration on the solid surface of the landing gear and on the refined mesh surface are compared.The findings indicate that the wall surface integration method exhibits significantly larger prediction deviations above 1 000 Hz in the high-frequency range compared to the refined surface method.Based on flow mechanism analysis,a noise reduction design method through flow rectification is proposed.By reshaping the geometry to suppress near-wall turbulence fluctuation intensity,the overall sound pressure level of landing gear noise is reduced by more than 5 dB across the 100～20 000 Hz frequency band.The research results provide theo-retical support for the refined prediction and flow control of aircraft landing gear aerodynamic noise.关键词
起落架/气动噪声/分离流/FW-H方程/流动控制Key words
landing gear/aerodynamic noise/separated flow/FW-H equation/flow control分类
航空航天引用本文复制引用
李蓝萱,郑国雨,董宁娟,黄江涛,乔磊,徐家宽,白俊强..大尺寸高保真起落架构型气动噪声预测及降噪控制[J].海军航空大学学报,2026,41(3):473-484,494,13.
