基于高阶谐波控制的倾转旋翼近场气动噪声主动控制试验  

Active control test of tiltrotor near-field aeroacoustics based on higherharmoniccontrol

作　　者：马锦超 陆洋[2] 王亮权 宋奎辉 MA Jinchao;LU Yang;WANG Liangquan;SONG Kuihui(Schoolof Mechanical Technology,Wuxi Institute of Technology,Wuxi 214121,China;National Key Laboratory of Science and Technology on Rotorcraft Aero-Mechanics,Nanjing university of aeronautics and astronautics,Nanjing 210016,China;Rotor Aerodynamics Key Laboratory,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]无锡职业技术学院机械工程分院,无锡214121 [2]南京航空航天大学直升机旋翼动力学重点实验室,南京210016 [3]中国空气动力研究与发展中心旋翼空气动力学重点实验室,绵阳621000

出　　处：《航空学报》2024年第9期229-239,共11页Acta Aeronautica et Astronautica Sinica

基　　金：中国空气动力研究与发展中心旋翼空气动力学重点实验室研究开放课题资助(RAL202103-3)。

摘　　要：倾转旋翼飞行器的桨尖靠近机身,其近场气动噪声问题严重,理论研究表明,高阶谐波控制能够调整桨盘载荷分布,从而降低倾转旋翼对机身表面的气动噪声辐射。通过试验研究验证了高阶谐波控制(HHC)对倾转旋翼飞行器近场气动噪声的抑制效果。研制了一套用于模型倾转旋翼的HHC伺服控制系统,及倾转旋翼飞行器缩比机身模型;进一步在消声室环境下搭建了倾转旋翼飞行器近场气动噪声主动控制的HHC主动控制试验系统,开展了直升机模式下的噪声主动控制试验研究;验证了HHC对倾转旋翼飞行器近场气动噪声的主动控制效果。试验结果表明2Ω的HHC控制输入的降噪效果最好,在直升机模式下,机身顶部观测点处的近场气动噪声最多可降低4.5 dB。The proximity of tiltrotor aircraft blade tips to the fuselage causes a serious near-field aeroacoustics prob-lem.Theoretical research shows that Higher Harmonic Control(HHC)input can adjust the load distribution of the rotor disc,thereby reducing the aeroacoustics radiation on the fuselage surface.In this paper,the suppression effect of HHC on near-field aeroacoustics in tiltrotor aircraft is verified experimentally.An HHC servo control system for model tiltrotor aircraft and a scaled fuselage model for tiltrotor aircraft are developed.An HHC active control test platform for near-field aeroacoustics in tiltrotor aircraft is further built in the anechoic chamber environment,and noise active control tests are carried out in helicopter mode.The active control effects of HHC on near-field aeroacoustics in tiltrotor aircraft are verified.The test results demonstrate that the 2 HHC control input yields the best noise reduction performance.In helicopter mode,the near-field aeroacoustics at the observation point on the top of the fuselage can be reduced by up to 4.5 dB.

关 键 词：倾转旋翼 高阶谐波控制 近场 气动噪声 主动控制 

分 类 号：V216.54[航空宇航科学与技术—航空宇航推进理论与工程]