A study on the strength of adhesively bonded joints with different adherends |
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| Affiliation: | 1. Dept. of Mechanical Eng., Atatürk Üniversity, 25240 Erzurum, Turkey;2. Dept. of Mechanical Eng., Erzurum Technical University, 25050 Erzurum, Turkey;3. EMYO, Atatürk Üniversity, 25240 Erzurum, Turkey;4. Dept. of Mechanical Eng., Batman Üniversity, 72100 Batman, Turkey;1. Department of Mechanics, Mathematics and Management (DMMM), Politecnico di Bari, Viale Japigia 182, 70126, Bari, Italy;2. Enea Research Centre Brindisi, SS 7 “Appia” km 714, 72100 Brindisi, Italy;1. Rzeszow University of Technology, Faculty of Mechanical Engineering and Aeronautics, al. Powstańców Warszawy 8, 35-959 Rzeszów, Poland;2. West Pomeranian University of Technology, Institute of Organic Chemical Technology, ul. Pulaskiego 10, 70-322 Szczecin, Poland;1. Dept. of Mechanical Eng., Ataturk University, 25240 Erzurum, Turkey;2. Dept. of Mechanical Eng., Erzurum Technical University, 25050 Erzurum, Turkey;3. Dept. of Mechanical Eng., Erzincan University, 24100 Erzincan, Turkey;4. Turkish Airlines Technic Inc., Istanbul, Turkey;1. Departamento de Engenharia Mecânica, Instituto Superior de Engenharia do Porto, Instituto Politécnico do Porto, Rua Dr. António Bernardino de Almeida, 431, 4200-072 Porto, Portugal;2. Departamento de Engenharia Mecânica, Faculdade de Engenharia da Universidade do Porto, Rua Dr. Roberto Frias, s/n, 4200-465 Porto, Portugal;3. Department of Mechanical and Aerospace Engineering, Politecnico di Torino, corso Duca degli Abruzzi 24, 10124 Torino, Italy |
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| Abstract: | In this study, mechanical properties of adhesively bonded single-lap joint (SLJ) geometry with different configurations of lower and upper adherends under tensile loading were investigated experimentally and numerically. The adherends were AA2024-T3 aluminum and carbon/epoxy composite with 16 laminates while, the adhesive was a two-part liquid, structural adhesive DP 460. In experimental studies, four different types of single-lap joints were produced and used namely; composite–composite (Type-I) with lower and upper adherends of the same thicknesses and four different stacking sequences, composite–aluminum (Type-II) with lower and upper adherends of the same thicknesses and four different stacking sequences, composite–aluminum (Type-III) with lower adherend (composite) of the same thickness but upper adherend of three different thicknesses, aluminum–aluminum (Type-IV) with lower adherend of the same thickness but upper adherend of three different thicknesses, composite–composite (Type-V) with [0]16 stacking sequences and three different overlap length, aluminum–aluminum (Type-VI) with three different overlap length. In the numerical analysis, the composite adherends were assumed to behave as linearly elastic materials while the adhesive layer and aluminum adherend were assumed to be nonlinear. The results obtained from experimental and numerical analyses showed that composite adherends with different fiber orientation sequence, different adherend thicknesses and overlap length affected the failure load of the joint and stress distributions in the SLJ. |
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| Keywords: | A. Carbon–carbon composites (CCCs) B. Stress concentrations C. Finite element analysis (FEA) D. Mechanical testing E. Joints/joining |
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