Abstract
The present paper treats an identification method of bending stiffness components of symmetric laminates using vibration data that consist of the low natural frequencies and the corresponding vibration modes. The present method is based on the virtual work principle and the least squares method, and it can give a nondestructive evaluation of bending stiffness components of laminated composites within a large-scale structure such as a wing structure. The method is applied to symmetrically laminated carbon/epoxy plates. The five bending stiffness components of laminated composites are identified using the vibration data obtained by a holographic apparatus. It is also numerically shown that the present method gives a precise evaluation of bending stiffness components insensitive to measurement errors.
