CAJ | 학술논문

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。
침대재풍동폐구시험단대 C919、MA700등민궤진행항공성학정위시험적수구，수선채용성츤시험단、파속형성맥극풍상위진렬산법、대각이제반권적방법화성압급적분방법등조시，해결폐구시험단존재적배경조성교고、기류대맥극풍측량간우문제，연후채용 MA60비궤모형진행료험증성풍동시험。풍동시험결과표명，성츤시험단유리우재폐구시험단내안장전성기상위진렬、전성기선진등측량설비，동시배경조성교상규폐구시험단현저강저，강조량체5～10dB；MA60비궤모형항공성학정위시험결과량급합리、규률정학，주요성원집중재금익위치。저표명，재 FL-9풍동폐구시험단건립료항공성학시험배경화조성원정위시험기술，가이승담궤체기동조성정위、강조기술험증등민궤형호연제급수적항공성학시험。
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 ar-ray beamforming algorithm and diagonal removal deconvolution was adopted to deal with the high background noise and flow interference to microphones in the closed test section.MA60 model test was carried out for validation.Test results show that the acoustic liner is in favour of micro-phone 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 re-sults,FL9 is capable of locating source and taking aeroacoustic experiments of airframe source lo-calization,noise reduction technique validation in the development of civil aircrafts.