Parametric Study of PEKK Based Fiber Metal Laminates Used in Aerospace Applications


Numerical analyses offer a cost-effective and efficient alternative to experimental investigations, and Finite Element (FE) models have become a popular tool to simulate the behavior of Fiber metal laminates (FMLs) under impact loads. This study verified the reliability of the proposed FE models to predict the perforation response of the FMLs investigated under low-velocity impact loadings. The validation of the FE models was assessed through comparison with the corresponding results of the experimental work. The results showed that the proposed simulations are capable of predicting the dynamic response of the laminates investigated with a high degree of success. The parametric studies were conducted on 2/1 titanium FMLs based on 2-ply composite cores and 2/1 aluminum FMLs based on 4-ply composite cores under impact with a variety of loading conditions. The developed FE models were then used to explore the structural behavior of the fiber metal laminates investigated with an extended variation of parameters, i.e., projectile striking angle, impact locations, the geometry of the projectile, and velocity. The results of the FEmodels are presented in terms of load-displacement traces, energy absorption,and failure modes. The findings of this study contribute to the understanding ofthe structural behavior of FMLs under impact loads and can inform the designand optimization of FMLs for various engineering applications. The use of FEmodels provides a cost-effective and efficient means of exploring the structuralbehavior of FMLs under different impact conditions, which can reduce the needfor costly and time-consuming experimental investigations.