基于微穿孔板的模型直升机舱内降噪研究
Reduction of Model Helicopter Cabin Noise Based on Micro-perforated Panel
李程磊 1陆洋 1李森琛 2马锦超1
作者信息
- 1. 南京航空航天大学航空学院 南京,210016
- 2. 武汉第二船舶设计研究所 武汉,430205
- 折叠
摘要
为验证微穿孔板吸声结构对直升机舱内噪声抑制的可行性和有效性,基于某轻型直升机模型机舱,开展了仿真与试验研究.首先,给出了适用于直升机舱内壁板的典型微穿孔板吸声结构方案;其次,建立了主减速器/机体声振耦合有限元模型,得到了微穿孔板吸声结构的设计频率范围,并通过仿真验证了吸声效果;最后,搭建了安装有微穿孔板吸声结构的模型直升机机舱试验平台,开展了舱内噪声试验研究.结果表明,在机舱内安装微穿孔板吸声结构后,相比于未安装微穿孔板机舱,在800～1 000 Hz和1 200～2 000 Hz的频率范围内,均具有优良的舱内降噪效果,最大噪声衰减量超过20 dB.
Abstract
In order to verify the feasibility and effectiveness of the micro-perforated panel absorber structure for noise suppression in helicopter cabin,simulation and experimental research are carried out based on a light heli-copter model cabin.Firstly,a typical structure of a micro-perforated panel absorber suitable for the inner wall of a helicopter cabin is given.A finite element model of the main gearbox/airframe acoustic-vibration coupling is further established.The design frequency range of the micro-perforated panel absorber structure is obtained,and the sound absorption effect is verified by simulation.Finally,a model helicopter cabin test platform installed with the micro-perforated panel absorber structure is built,and noise test in the cabin is carried out.The test re-sults show that after installing the micro-perforated panel absorber structure in the cabin,compared with the cabin without the micro-perforated panel,cabin with such structure has an excellent effect on reduction of cabin noise in the frequency range of both 800～1 000 Hz and 1 200～2 000 Hz,in which the maximum attenuation are more than 20 dB.
关键词
直升机/舱内降噪/微穿孔板/吸声结构/声场分析Key words
helicopter/reduction of cabin noise/micro-perforated panel/sound absorption structure/sound field analysis引用本文复制引用
基金项目
国家重点研发计划资助项目(2021YFB3400100)
出版年
2024
NETL
NSTL
万方数据