Analysis for Natural Frequency and Mode Shape of Wing Structure

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.