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提出一种改进的飞行器动弯矩识别方法,该方法引入了频域积分算法,避免了时域方法中消除趋势项以及滤波所带来的问题。对加速度响应进行两次积分得到结构弹性位移响应,然后根据模态叠加理论求解出广义坐标,最后结合模态弯矩识别截面的动弯矩响应。通过悬臂梁试验验证了算法的有效性,并与传统方法识别出的结果进行对比。结果表明,新方法的识别结果更接近试验实测动弯矩响应,具有更高的精度。最后将该方法应用于某型号飞行器,并给出了识别结果。
An improved aircraft dynamic moment identification method is proposed. This method introduces the frequency domain integration algorithm, which avoids the problems caused by eliminating trend items and filtering in the time domain method. Integrate the acceleration response twice to get the elastic displacement response of the structure. Then, the generalized coordinates are solved according to the modal superposition theory. Finally, the dynamic bending moment response of the cross section is recognized with the modal bending moment. The validity of the algorithm is verified by the cantilever test and compared with the results of traditional methods. The results show that the recognition result of the new method is closer to the experimental dynamic bending moment response with higher precision. Finally, the method is applied to a certain type of aircraft and the recognition result is given.