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Abstract Fiber metal laminates (FMLs) are widely applied as protective structures in various high-tech industries owing to their excellent impact resistance. This paper presents an explicit finite element (FE) simulation to investigate the dynamic damage behavior of carbon fiber-reinforced aluminum laminates (CRALLs) under combined explosion and fragment loading. Johnson-Cook model is utilized to capture the damage response of aluminum material; 3D Hashin failure criteria are applied to predict the damage evolution of fiber composite material considering the high strain rate effect; cohesive elements are incorporated to simulate the inter-laminar delamination phenomena. The effectiveness of the proposed numerical model is verified through a comparison with available experimental data in ballistic impact conditions. In addition, a thorough analysis of the dynamic behavior and damage mechanism of FMLs is conducted, and the impact performance is extensively discussed in terms of the influences of explosion distance and explosion mass. This work serves as a valuable reference for future numerical studies on the explosive impact resistance of other FMLs structures. [ABSTRACT FROM AUTHOR]

The low-velocity impact resistance of fiber metal laminates (FMLs) is investigated. FMLs with titanium alloy Ti-6Al-4V sheets and glass fiber/epoxy layers are fabricated using the hand layup technique, exhibiting the same total metal layer thickness. A drop tower is used to produce a low-velocity impact on the FMLs. FML with outermost metallic layers exhibits comparatively higher lateral spreading and interlayer delamination opening contrary to FML with more metallic layers. This is also observed in high-velocity impact. The low-velocity impact resistance of titanium-based FMLs seems higher than aluminum-based FMLs. This is also noticed in high-velocity impact for former and latter FMLs. [ABSTRACT FROM AUTHOR]

Mechanical properties and load vs. displacement diagrams, and fatigue life, mechanisms and load vs. cycles curves were received for fiber metal laminates (FMLs) with original and inclined edge cracks at room and elevated temperatures. The mixed mode stress intensity factors and J-integral of cracked FMLs were obtained. The bridging stresses was considered in the modified Paris Law to predict fatigue life of inclined crack FMLs. The predicted results of fatigue life with vertical cracks at room temperature were satisfactorily well. The fatigue life of samples with inclined cracks at elevated temperature the scatter was also acceptable within minor errors. [ABSTRACT FROM AUTHOR]

The current work investigates the influences of different surface modifications on the flexural characteristics of carbon fiber reinforced aluminum (AA2024-T3) laminates fabricated at 3/2 sequence. Among all types of surface modifications, mechanical abrasion by 220-grit paper shows highest flexural strength. The flexural load of Al/0°/Al/0°/Al configuration is about 19% higher in comparison with mechanical abrasion (220-grit paper) with chemical treatment due to higher interfacial strength. However, corrosion resistance is improved about 30 times in the later modification. In-situ imaging reveals that failure of Al/0°/Al/0°/Al laminates initiates by micro-buckling of carbon fiber whereas matrix cracking initiates the failure in Al/90°/Al/90°/Al laminates. [ABSTRACT FROM AUTHOR]