具有波浪形桨尖构造的无人机旋翼降噪研究  

Noise reduction of the unmanned aerial vehicle rotor with wavy tip structure

作　　者：张小正[1] 王雅洁 李家柱[1] 毕传兴[1] 徐滢 ZHANG Xiaozheng;WANG Yajie;LI Jiazhu;BI Chuanxing;XU Ying(Institution of Sound and Vibration Research,Hefei University of Technology,Hefei 230009,China)

机构地区：[1]合肥工业大学噪声振动工程研究所,合肥230009

出　　处：《振动与冲击》2024年第22期135-145,共11页Journal of Vibration and Shock

基　　金：国家自然科学基金面上项目(51875147,12174082)。

摘　　要：旋翼作为无人机噪声的重要来源,降低其气动噪声对于提高公众对无人机的接受度具有重要意义。鉴此,提出一种具有波浪形桨尖构造的旋翼设计方案,该方案仅在旋翼桨尖处以特定波浪线型为导线进行放样设计,同时耦合波浪形前缘、波浪形尾缘和波浪表面结构三种特征,该方案可在降低噪声的同时,最大程度保留旋翼气动性能。随后通过计算流体动力学仿真以及试验研究分析波浪形桨尖构造对旋翼气动性能以及气动噪声的影响,揭示其降噪机理,并开展波浪形桨尖参数优化设计。仿真和试验结果表明:具有波浪形桨尖构造的旋翼仍然具有较好的气动性能;在声学性能方面,波浪形桨尖构造降低了旋翼中高频范围内的宽带噪声,其中波形参数N=8的旋翼降噪效果最好,并在旋翼下洗流附近降噪显著,总声压级较Base旋翼下降1.5~4.0 dB。As an important source of unmanned aerial vehicle noise,reducing the aerodynamic noise of its rotor is of great significance to improve the public's acceptance of unmanned aerial vehicle.In view of this,a rotor design scheme with the wavy-shaped blade tip structure was proposed.In the scheme,only a specific wave line type was used as the wire in the lofting design at the blade tip of the rotor,and also the three characteristics of wavy-shaped leading edge,wavy-shaped trailing edge and wavy surface structure were coupledly adopted.This scheme can reduce the noise and retain the aerodynamic performance to the greatest extent.The influence of wavy blade tip structure on rotor aerodynamic performance and aerodynamic noise were analyzed with computational fluid dynamics simulation and experimental investigation.The noise reduction mechanism was revealed,and the parameter optimization design of the wavy tip was carried out.The simulation and experimental results show that the rotor with wavy tip structure still has good aerodynamic performance.In terms of acoustic performance,the wavy blade tip structure reduces the broadband noise in the middle and high frequency ranges of the rotor.The rotor with waveform parameter N=8 has the best noise reduction effect,and the noise reduction is significant near the downwash flow of the rotor.The total sound pressure level is 1.5-4.0 dB lower than that of the Base rotor.

关 键 词：无人机旋翼 降噪设计 气动性能 气动声学 计算流体动力学仿真 

分 类 号：TB53.5[理学—物理]