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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。
In order to meet the requirements of aeronautical acoustics positioning tests on civil aircraft such as C919 and MA700 in the closed-hole test of wind tunnel, the acoustic lining test section, the beamforming microphone phase array algorithm, the diagonal removal deconvolution method and the sound pressure level integration method And other measures to solve the closed-end test section there is a high background noise, airflow interference measurement of the microphone, and then use the MA60 aircraft model validation wind tunnel test. The wind tunnel test results show that the acoustic lining test section facilitates the installation of measuring instruments such as microphone phase array and microphone array in the closed test section, and significantly reduces the background noise compared with the conventional closed-end test section with the noise reduction of 5 to 10 dB. The MA60 aircraft The results of the model aeronautical acoustic localization test are reasonable in magnitude and correct in law. The main sound sources are concentrated at the flap positions. This indicates that an aeronautical acoustic test environment and a noise source localization test technology are established in the closed section of the wind tunnel of FL-9, which can undertake aeronautic acoustical tests urgently needed for the development of civil aircraft models such as aerodynamic noise localization and noise reduction technology verification.