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 Fiber Aluminum Laminate (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.