悬停状态电控旋翼噪声主动控制试验  

Noise Active Control of Electriccally Controlled Rotor in Hover

作　　者：卫瑞智 陆洋[1] 董祥见 冯剑波[1] WEI Ruizhi;LU Yang;DONG Xiangjian;FENG Jianbo(National Key Laboratory of Science and Technology on Rotorcatt Aeromechanics,Nanjing University of Aeronautics&Astronautics,Nanjing,210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210016

出　　处：《南京航空航天大学学报》2018年第2期258-265,共8页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(51375229)资助项目

摘　　要：为研究电控旋翼襟翼高阶谐波噪声控制规律,在电控旋翼综合试验台上进行了悬停状态下的噪声主动控制试验。首先搭建了用于旋翼噪声测量和襟翼控制的测控系统,基于该系统,施加了不同谐波阶数下的襟翼幅值、相位控制,通过对试验数据的分析表明:旋翼转速为500r/min时,旋翼噪声声压级最多可降低4dB;最佳的旋翼噪声控制襟翼谐波阶数为2/rev,襟翼谐波的最优控制幅值小于6°,最优控制相位在180°~300°之间。In order to study the high harmonic control for the noise reduction of the electrically controlled rotor,the active noise control experiments are carried out based on the electronic controlled rotor test rig.Rotor noise measurement system and the flap control system are built firstly.On the basis,the am-plitude and phase control of different harmonics are carried out in the experiments.The experimental re-sults show that the rotor sound pressure level can be reduced by 4 dB when the rotor rotating speed is 500 r/min;the optimal control harmonic occurr at 2/rev;the optimal control harmonic amplitude is less than 6°,and also the optimal control phase happen between 180°-300°.

关 键 词：电控旋翼 襟翼 噪声 主动控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]