면내하중을 받는 보강된 복합적층판의 진동 해석

Abstract

The vibration analysis of stiffened composite laminates subjected to inplane forces has been performed by the finite element method based on the 1st order shear deformable plate theory. The applied compressive in-plane forces decrease the natural frequencies of the composite laminates because the laminates under compressive loads become flexible in the transverse direction. When the in-plane load increases up to the critical buckling value. the frequency of any one mode becomes zero. and its mode shape becomes the buckling one. It is found that the moment of inertia of a stiffener. and the fiber orientation affect significantly the natural frequencies of stiffened composite laminates subjected to in-plane loading.