无轴承旋翼摆振模态阻尼识别技术研究及其应用  

Damping identification technique for helicopter bearingless rotor blades' lead-lag mode

作　　者：张仕明 周云[1] 胡和平[1] ZHANG Shiming;ZHOU Yun;HU Heping(Key Lab of Helicopter Rotor Dynamics,CHRDI,Jingdezhen 333000,China)

机构地区：[1]直升机旋翼动力学重点实验室,中国直升机设计研究所,江西景德镇333000

出　　处：《振动与冲击》2018年第19期225-230,共6页Journal of Vibration and Shock

基　　金：国家863计划:先进直升机技术(2012AA112201)

摘　　要：旋翼桨叶的一阶摆振后退型模态是影响直升机地面共振稳定性的主要模态。为了识别装机状态下桨叶一阶摆振模态阻尼,该研究发展了基于FFT分析的移动矩形窗法、基于Fourier级数的移动矩形窗法、基于希尔伯特变换法和基于Wavelet小波变换等四种方法的无轴承旋翼一阶摆振模态阻尼识别技术,针对试验中测得的信号出现的频率成分密集和信噪比差等情况在阻尼识别过程中增加了数字滤波器,数值仿真和基于装机试验数据的识别均表明,基于Fourier级数的移动矩形窗和基于Wavelet小波变换两种阻尼识别技术可有效分离无轴承旋翼摆振模态,数字滤波器可有效提高桨叶摆振阻尼识别精度。Helicopter rotor blades’first order lead-lag backward type mode is the main mode to affect its ground resonance stability.To identify the damping of this first order lead-lag mode,four different methods including FFT-based moving block(FFT-MB),Fourier series-based moving block(FSMB),Hilbert transform(HT)and Wavelet transform(WT)were proposed.Aiming at measured signals appearing dense frequency components and had signal-noise-ratio(SNR),a digital filter was added.Numerical simulation and recognition results based on test data indicated that both FSMB and WT methods can be used to effectively separate the first order lead-lag mode of helicopter bearingless rotor blades and the digital filter can be used to effectively improve the damping identification accuracy of this lead-lag mode.

关 键 词：旋翼 无轴承 阻尼识别 摆振 滤波 

分 类 号：V216.21[航空宇航科学与技术—航空宇航推进理论与工程]