Experimental and Numerical Investigation of Mechanical and Modal Behavior of Hybrid Fiber Metal Laminates for Aerospace Applications

ABSTRACT This study examines the tensile, axial compression (buckling), flexural, and modal behavior of three aerospace‐grade fiber metal laminates (FMLs): GLARE, CARALL, and a newly developed hybrid laminate (C‐GLARE). All laminates were fabricated using a wet lay‐up process, and their mechanical performance was evaluated following standard testing procedures. Modal characteristics were obtained under cantilever and simply supported boundary conditions, and the results were validated through finite element simulations. The hybrid C‐GLARE laminate exhibited improved damping capacity and flexural strength compared to CARALL, particularly in the 0° fiber orientation. Among the laminates, GLARE showed the highest damping ratio, followed by C‐GLARE and CARALL. The lower lateral tensile performance of carbon/epoxy, as observed in CARALL, was consistent with the experimental findings. Simply supported specimens demonstrated higher natural frequencies due to increased boundary restraint. Overall, the C‐GLARE laminate displayed superior combined mechanical and dynamic performance, indicating its potential suitability for aerospace structural applications, especially in upper fuselage components requiring enhanced strength and vibration damping.