• Jappes, J. T. Winowlin
• Hynes, N. Rajesh Jesudoss
• Pruncu, Catalin I.
• Ali, Muhammad Asad
• Barile, Claudia
• Vignesh, N. J.
• Farooq, Muhammad Umar
• Velu, P. Shenbaga

Abstract

<p>Fibre Metal Laminates are structures used primarily in aerospace applications because of their principal advantages such as high strength, lower density, and impact resistance. In the present work, a systematic assessment has been made to evaluate two different stacking sequences of FMLs (Type – I (AA 6061/Carbon Fibre/AA 6061/Carbon Fibre/AA 6061), and Type – II (Carbon Fibre/AA 6061/Carbon Fibre/AA 6061/Carbon Fibre)) against a pure carbon composite (Type - III) as baseline for improvement. The investigations are made for enhanced impact resistance, improved tensile strength, increased flexural capability, microstructural evolution, and surface composition. Mechanical-based testing resulted that Type – I shows significant performance followed by Type – II. The maximum values of tensile strength, impact test, and ultimate load bearing capacity of during flexural test were around 192.92 MPa, 9.3 J, and 155 N, respectively. Correlations of experimental results were drawn against numerical simulation to validate the tensile and flexural results. Microstructural evolution indicated good bonding capability of Type – I FML with the carbon fibre. EDX analysis was carried out analyse surface chemistry. Selected Fibre Metal Laminate sequence can help in improving aeronautical industry's structural applications because of good ductile properties together with fatigue strength and impact resistance.</p>

Topics

• density
• surface
• Carbon
• simulation
• strength
• fatigue
• composite
• bending flexural test
• impact test
• Energy-dispersive X-ray spectroscopy
• tensile strength