某机翼结构的固有频率和振型分析

Analysis for Natural Frequency and Mode Shape of Wing Structure

摘要: 本文采用有限元和试验对某一无人机复合材料机翼的固有频率和振型进行仿真和实验分析。通过利用非接触式激光测振仪设备，为了消除边界条件对机翼结构振动特性的影响，采用自由边界条件进行了机翼振动特性测量，获得了复合材料机翼的前4阶固有频率和振型。同时对比了有限元仿真结果。计算结果表明，仿真结果与试验测试结果基本一致。

Abstract: In this electronic document, the FEM is used to simulate and analyze the natural frequency and vibration mode of a certain UAV composite wing. By using the non-contact laser vibrometer equipment, in order to eliminate the influence of boundary conditions on the vibration characteristics of the wing structure, the vibration characteristics of the wing are measured by free boundary conditions, and the first 4 natural frequencies and vibrations of the composite wing are obtained. At the same time, the finite element simulation results are compared. The calculation results show that the simulation results are basically consistent with the experimental results.