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作 者:梁宁远 陈宝[1,2] 韩松辰 陈佳伟 王玉琢 王普缘 Liang Ningyuan;Chen Bao;Han Songchen;Chen Jiawei;Wang Yuzhuo;Wang Puyuan(Heilongjiang Provincial Key Laboratory of Aerodynamic Noise and Control,AVIC Aerodynamics Research Institute,Harbin 150001,China;Low Speed and High Reynolds Number Aeronautical Key Laboratory,Harbin 150001,China)
机构地区:[1]中国航空工业空气动力研究院,黑龙江省空气动力噪声及其控制重点实验室,黑龙江哈尔滨150001 [2]低速高雷诺数航空科技重点实验室,黑龙江哈尔滨150001
出 处:《航空科学技术》2023年第9期41-51,共11页Aeronautical Science & Technology
摘 要:针对高速直升机旋翼噪声传入舱内引起的舒适性问题,本文开展了舱内噪声主动控制技术研究。根据高速旋翼噪声数值计算结果,在实验室环境中通过声源模拟系统采用声压匹配法重构了直升机地面模拟舱飞行状态的外部声场。对噪声主动控制算法进行仿真分析,本文研究了算法对低频线谱噪声的降噪性能,并提出了一种试验与仿真相结合的主动噪声控制系统扬声器与传声器布放优化方法,对比不同布放组合方案下的理论降噪量,通过直升机舱内主动噪声控制验证试验,取得了实验室环境5个误差点处0~1000Hz范围内平均12.7dB总声压级的降噪效果。In view of the serious noise problem caused by the transmission of rotor noise into the cabin of high-speed helicopters,the research on active control technology of interior noise was carried out.According to the calculation results of rotor noise,the sound field of the flight state was reconstructed outside the helicopter ground simulation cabin in the laboratory environment by sound pressure matching method using the sound source simulation system.The noise active control algorithm was simulated analyzed,and the noise reduction performance of the algorithm on low-frequency line spectrum noise was studied.An optimization method for speaker and microphone placement of active noise control system combining test and simulation was proposed,and the theoretical noise reduction that can be obtained under different placement combination schemes is compared.According to the simulation analysis and test results,the active noise control in the helicopter cabin was implemented,and the noise reduction effect of the average total sound pressure level of 12.7dB in the range of 0~1000Hz at the five error points of the laboratory environment was obtained.
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