TY - JOUR
T1 - Effect of stacking sequence of fibre metal laminates with carbon fibre reinforced composites on mechanical attributes
T2 - numerical simulations and experimental validation
AU - Hynes, N. Rajesh Jesudoss
AU - Vignesh, N.J.
AU - Jappes, J.T. Winowlin
AU - Velu, P. Shenbaga
AU - Barile, Claudia
AU - Ali, Muhammad Asad
AU - Farooq, Muhammad Umar
AU - Pruncu, Catalin I.
PY - 2022/4/12
Y1 - 2022/4/12
N2 - 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.
AB - 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.
KW - carbon fibre composites
KW - fibre metal laminates
KW - mechanical testing
KW - microstructural analysis
KW - numerical simulation
UR - http://www.scopus.com/inward/record.url?scp=85125498247&partnerID=8YFLogxK
U2 - 10.1016/j.compscitech.2022.109303
DO - 10.1016/j.compscitech.2022.109303
M3 - Article
AN - SCOPUS:85125498247
VL - 221
JO - Composites Science and Technology
JF - Composites Science and Technology
SN - 0266-3538
M1 - 109303
ER -