Flight Flutter Modal Parameters Identification with Atmospheric Turbulence Excitation Based on Wavelet Transformation

针对基于大气紊流激励的飞机颤振试验数据具有信噪比低以及测量数据以加速度响应形式给出等特点,将小波变换与随机减量法相结合对飞机颤振模态参数进行识别,首先利用随机减量法获得结构在非零初始加速度条件下的自由衰减响应,然后对该自由衰减响应进行Morlet连续小波变换,为使变换简单,本文采用了Parseval定理和留数定理,利用Morlet的带通滤波特性,通过搜索小波变换系数在不同的尺度区域内的极大值,再根据小波变换系数的极大值、相角与固有振动频率及阻尼系数间的关系,即可识别出各模态参数。并对利用小波变换识别颤振模态参数时,实现模态解耦应满足的条件进行了分析研究。通过仿真和飞机颤振试验数据分析,验证了该识别方法不仅简单、有效和可行,而且具有较强的抗噪性。

Flight Flutter Modal Parameters Identification with Atmospheric Turbulence Excitation Based on Wavelet Transformation

In view of the feature of flight flutter test data with atmospheric turbulence excitation, a method which combines wavelet transformation with random decrement technique for identifying flight flutter modal parameters is presented. This approach firstly uses random decrement technique to gain free decays corresponding to the acceleration response of the structure to some non-zero initial conditions. Then the continuous Morlet wavelet transformation of the free decays is performed; and the Parseval formula and residue theorem are used to simplify the transformation. The maximal wavelet transformation coefficients in different scales are searched out by means of band-filtering characteristic of Morlet wavelet, and then the modal parameters are identified according to the relationships with maximal modulus and angle of the wavelet transform. In addition, the condition of modal uncoupling is discussed according to variation trend of flight flutter modal parameters in the flight flutter state. The analysis results of simulation and flight flutter test data show that this approach is not only simple, effective and feasible, but also having good noise immunity.