A CDM-based failure model for predicting strength of notched composite laminates |
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| Affiliation: | 1. DEMec, Faculdade de Engenharia, Universidade do Porto, Rua Dr. Roberto Frias, s/n, 4200-465 Porto, Portugal;2. INEGI, Universidade do Porto, Rua Dr. Roberto Frias, 400, 4200-465 Porto, Portugal;3. Matthias Vogler Engineering & Consulting Services, Sauerweinstr.3, 30167 Hannover, Germany;1. Monash University, Department of Mechanical and Aerospace Engineering, Clayton Campus, Victoria 3800, Australia;2. Cooperative Research Centre for Advanced Composite Structures, 1/320 Lorimer Street, Port Melbourne, Victoria 3207, Australia;3. Queen’s University Belfast, School of Mechanical and Aerospace Engineering, Belfast, BT9 5AH, UK;4. University of Liège, Aerospace and Mechanical Engineering Department, 1 chemin des, Chevreuils, 4000 Liège, Belgium;1. Department of Aerospace Engineering, Tohoku University, 6-6-01, Aoba-yama, Aoba-ku, Sendai, Miyagi 980-8579, Japan;2. Structures and Advanced Composite Research Unit, Aeronautical Technology Directorate, Japan Aerospace Exploration Agency (JAXA), 6-13-1 Osawa, Mitaka, Tokyo 181-0015, Japan;3. Department of Mechanical Engineering, National University of Singapore, 21 Lower Kent Ridge Road, 119077 Singapore, Singapore |
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| Abstract: | This paper investigates the ultimate tensile failure strength of laminated composites containing a central circular hole. Based on continuum damage mechanics, a Principal Damage Model is developed by combining the generalized standard material model with the Principal Damage concept of composite materials. Three in-plane failure modes: fiber breakage, matrix cracking, and fiber/matrix interface debonding are included in the present model. After obtaining material constants and damage relations from standard tensile tests, the material constitutive relations with damage model are implemented into commercial finite element code, abaqus. By comparing the predicted results with the experimental data, the proposed model has proven to be capable of predicting failure strength and load–deflection relations of notched laminated composites. The effects of hole size and specimen width are discussed in detail. In addition, the advantage of the present model is demonstrated through comparison with other existing models. |
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