Numerical investigation of glass laminate aluminium reinforced epoxy (GLARE) composite to impact loading

Abstract

The aerospace industry is consistently in persistent need of lightweight materials for which, fiber metal laminates (FMLs) have arisen as an innovative solution by combining the ductility of metals and strength of composites. Glass laminate aluminum reinforced epoxy (GLARE), a commonly used fiber metal laminate in aircraft structures, is often exposed to low-velocity impact incidents. A study of the dynamic response of GLARE under repeated low-velocity impacts is presented in the paper. The studied fiber metal laminate consists of two layers of glass fiber-reinforced plastics alternately sandwiched between three layers of aluminum 2024 alloy. A finite element (FE) model is developed, incorporating interface modeling, contact modeling, and failure considerations, validated against published experimental results. Four distinct impact energy scenarios are examined, comparing the damage patterns of GLARE composites concerning the precision and efficiency of the numerical model. The validated model is then utilized to explore the effect of impact of energy on energy absorption characteristics of GLARE. The analysis, conducted on ANSYS – AUTODYN software, contributes valuable insights for optimizing the design and structural considerations of GLARE in aerospace applications, particularly in situations involving repeated low-velocity impacts. Key results include an observed increase in indentation depth from 2.4 mm to 5 mm as impact velocity rises between 50-110 m/s, and energy absorption capacity improving from 0.4 MJ to 2.2 MJ respectively. Numerical predictions achieved high accuracy, with a marginal error of 3.24% compared to experimental data, confirming the model's reliability in replicating impact resistance and energy dissipation characteristics. The findings offer a framework for optimizing lightweight, high-strength materials for aerospace and other engineering applications.