Numerical Analysis of 3/2 Aluminium Carbon Fiber Laminate with Delamination to Study the Effect on Natural Frequency and Stiffness
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Abstract
Delamination is a common problem in fiber-metal laminate composite structures, which often go undetected and can reduce structural stiffness. Delamination is definitely a significant issue since it affects the functionality of Fiber Metal Laminates (FMLs) structures in use. In an industry such as aviation, identifying and evaluating delamination severity is crucial for both financial and safety reasons. The natural frequency, mode shapes, stiffness, and other vibration properties of composites are affected by the presence of delamination. As a result, the location and amount of delamination may be accurately determined using this signal. This paper uses a 3/2 aluminium carbon fiber laminate made up of three layers of aluminium and two layers of unidirectional carbon fiber. The current study utilises finite element analysis to examine the effect of delamination on the natural frequency and stiffness of 3/2 aluminium carbon fiber laminate beams using free vibration characteristics. The first six modes of natural frequency are obtained using finite element analysis. The stiffness is calculated and compared using two methods: vibration methods and deflection methods. Finite element analysis is done for both undamaged and damaged aluminium carbon fiber laminate. From the study, the natural frequency and stiffness are affected by the delamination.
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