摘要
针对在风洞闭口试验段对C919、MA700等民机进行航空声学定位试验的需求,首先采用声衬试验段、波束形成麦克风相位阵列算法、对角移除反卷积方法和声压级积分方法等措施,解决闭口试验段存在的背景噪声较高、气流对麦克风测量干扰问题,然后采用MA60飞机模型进行了验证性风洞试验。风洞试验结果表明,声衬试验段有利于在闭口试验段内安装传声器相位阵列、传声器线阵等测量设备,同时背景噪声较常规闭口试验段显著降低,降噪量达5~10dB;MA60飞机模型航空声学定位试验结果量级合理、规律正确,主要声源集中在襟翼位置。这表明,在FL-9风洞闭口试验段建立了航空声学试验环境和噪声源定位试验技术,可以承担机体气动噪声定位、降噪技术验证等民机型号研制急需的航空声学试验。
To meet the requirement of aeroacoustic localization experiment for civil aircrafts like C919 and MA700 in aero-acoustic wind tunnel tests, a liner test section featuring phased array beamforming algorithm and diagonal removal deconvolution was adopted to deal with the high background noise and flow interference to microphones in the dosed test section. MA60 model test was carried out for validation. Test results show that the acoustic liner is in favour of microphone phased array and line array installation in the closed test section, and the background noise is reduced to be about 5 - 10dB which is lower than that in traditional closed test sections. The sound pressure level and trend found in the localization tests are reasonable. Judging from the results, FL9 is capable of locating source and taking aeroacoustic experiments of airframe source localization, noise reduction technique validation in the development of civil aircrafts.
出处
《实验流体力学》
CAS
CSCD
北大核心
2015年第5期78-83,共6页
Journal of Experiments in Fluid Mechanics
关键词
航空声学
定位试验
声衬试验段
风洞试验
波束形成
aeroacoustics
source localization
lining test section
experiment in wind tunnel
beamforming
