Different analytical formulations are reported in recent works to model the failure strength and the progressive failure of different fiber metal laminates (FMLs). Although the basis for all these formulations is classical lamination theory (CLT), the models differ with each other while modeling the stiffness degradation. A common analytical formulation that is independent of configuration of the laminate will be very helpful for the designers in this field. Present work is aimed to develop such a model with the help of a hybrid degradation scheme, which uses constant degradation factors based on the condition of the adjacent lamina. This hybrid degradation scheme has helped to model the occurrence of multiple failures inside a lamina during failure progression. The formulation is tested with three types of FMLs and the results show that the formulation is very much helpful in predicting the failure strength and progressive failure.

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An analytical formulation is developed to estimate the strength of the fiber metal laminates (FML) consisting of cross-ply glass fiber reinforced plastic layers and aluminum sheets. Classical lamination theory is taken as basis for the formulation. A new degradation model based on Tsai-Hill terms is developed and used with analytical formulation to assess the progressive failure. Appropriate features are incorporated in the model to distinguish the matrix failure, the fiber matrix debonding, the fiber failure, and the failure of the isotropic layer. The formulation is used to predict the failure behavior of a FML under in-plane off-axis loading. Different strengths associated with the failure of the laminate like stress at first ply failure and yielding of isotropic layer are investigated. The results show that the new degradation model facilitated the detailed estimation of failure progression. These values of predicted strength are more accurate and closer to the actual experimental results than that of the values predicted by any other model.

Fibre Metal Laminates (FMLs) are laminates consisting of metal layers and fibre reinforced composite layers. These laminates are designed to improve some specific properties of constituent metals and composites layers. Estimation of First Ply Failure (FPF) Loads of these FMLs is a part in the broad characterization of these materials. A numerical method is developed for the estimation of FPF when these laminates are used as simply supported plates subjected to uniformly distributed load. Various failure criterions are used to identify these loads. The proposed method has been validated with the results of exact (Navier) solution available in the literature. FPFs are estimated for different groups of FMLs based on Aluminum, Titanium and Magnesium layers. The results are presented in the form of non-dimensional FPF and deformation values for various aspect ratios.