摘要
针对直升机舱内噪声控制问题,基于统计能量分析方法建立舱内噪声预测模型。通过在实际飞行条件下开展的试验获取声源激励输入参数,并结合舱内噪声实测结果验证模型的准确性。在已验证模型的基础上,开展舱内噪声传递路径及贡献分析,提出相应的降噪措施并分析降噪效果。研究结果表明:舱内噪声预测结果和实际测试结果一致,总声压级差异小于1 dB(A);在180 km/h匀速平飞工况下发动机舱是主要的噪声源,声能量通过防火墙传入舱内;分析发动机噪声变化对舱内噪声的影响,发现发动机噪声减小8 dB(A)时,舱内噪声减小3 dB(A)左右;在防火墙上喷涂2 mm阻尼浆后,驾驶位和乘员位的总声压级可分别降低0.7和0.8 dB(A)。相关结果可为直升机舱内减振降噪设计提供参考依据。
Aiming at the noise control problem in the helicopter cabin,a cabin noise prediction model was established based on the Statistical Energy Analysis method.The input parameters of the sound source excitation were obtained in combination with the actual flight test,and the accuracy of the model was verified with measured results of the cabin noise.Based on the verified model,the noise transmission path and contribution analyses in the cabin were carried out,the corresponding noise reduction measures were proposed and the noise reduction effect was analyzed.The research results show that the noise prediction in the cabin is consistent with the actual test results,and the difference in the total sound pressure level is less than 1 dB(A).Taking 180 km/h constant speed level flight as an example,it is found that the engine compartment has the main noise contribution,and the sound energy is transmitted into the cabin through the sound insulation path of the firewall.The impact of engine noise changes on the cabin noise is analyzed.It is found that the noise of the engine is reduced by 8 dB(A),and the noise in the cabin is reduced by about 3 dB(A).After spraying a 2 mm damping slurry on the firewall,the overall sound pressure level at the driver's seat and the passenger's seat positions can be reduced by 0.7 dB(A)and 0.8 dB(A),respectively.The relevant results may provide a reference for the design of vibration and noise reduction in the helicopter cabins.
作者
陈畅
姚丹
张玉梅
赵悦
庞杰
周长春
CHEN Chang;YAO Dan;ZHANG Yumei;ZHAO Yue;PANG Jie;ZHOU Changchun(College of Aviation Engineering,Civil Aviation Flight University of China,Guanghan 618307,Sichuan,China)
出处
《噪声与振动控制》
北大核心
2025年第5期196-201,共6页
Noise and Vibration Control
基金
四川省自然科学基金资助项目(2023NSFSC0902)
民航飞行技术与飞行安全重点实验室开放基金资助项目(FZ2022KF01)
中央高校基本科研业务费专项资金资助项目(PHD2023-009)
气动噪声控制重点实验室研究基金资助项目(ANCL20220202)。
关键词
声学
直升机
舱内噪声
降噪
统计能量分析
acoustics
helicopter
cabin noise
noise reduction
statistical energy analysis
