Abstract
Fibre metal laminate (FML) composites are hybrid structures made of various metal sheets and fibre reinforced polymer matrix composites. These materials are preferred in the aircraft, automobile, and aerospace industries due to their high performance. Therefore, it is crucial to examine the vibration behaviour in the design process. In this study, the vibration behaviours of FMLs are examined numerically and experimentally. Firstly, the governing equations of the FML plate are determined based on classical plate theory. The generalized differential quadrature method (GDQ) is used in numerical analysis. Then, to prove the accuracy of the numerical model, the natural frequencies are compared with the experimental results. It is seen that the numerical results are in good agreement with the experimental results. Finally, the effects of material properties, geometry, and different boundary conditions on the dynamic properties of the FML composites are investigated. The results indicate that as the number of aluminium layers in the structure increases, natural frequencies are also significantly affected. When the Al layers are moved from the surface to the centre, it causes a reduction in the first natural frequencies of the structure. Morever, the boundary conditions substantially impact the natural frequency of the FML plates.
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