Effect of stacking sequence of fibre metal laminates with carbon fibre reinforced composites on mechanical attributes: Numerical simulations and experimental validation

Fibre Metal Laminates are structures used primarily in aerospace applications because of their principal ad-vantages such as high strength, lower density, and impact resistance. In the present work, a systematic assess-ment 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 indi-cated 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.

Automated summary

This study evaluates two different stacking sequences of Fibre Metal Laminates (FMLs) and compares them with a pure carbon composite. The results show that one of the stacking sequences (Type - I) performs the best, with higher tensile strength, impact resistance, and flexural load bearing capacity.