Modelling complex progressive failure in notched composite laminates with varying sizes and stacking sequences |
| |
| Affiliation: | 1. Department of Mechanical Engineering, National University of Singapore, 9 Engineering Drive 1, Singapore 1175762, Singapore;2. Sir Lawrence Wackett Aerospace Research Centre, School of Aerospace Mechanical and Manufacturing Engineering, RMIT University, GPO Box 2476V, Melbourne 3001, Australia;1. University of Pittsburgh, Department of Civil and Environmental Engineering, United States;2. Bridge Management Unit, Pennsylvania Department of Transportation, United States;1. Department of Mechanical Engineering, National University of Singapore, 21 Lower Kent Ridge Road, Singapore 119077, Singapore;2. Department of Aeronautics, South Kensington Campus, Imperial College London, London SW7 2AZ, United Kingdom;1. College of Field Engineering, PLA Army Engineering University, No. 1 Haifuxiang, Qinhuai District, Nanjing, Jiangsu Province, China;2. Institute of Process Equipment, Zhejiang University, China;3. Department of Airfield Logistics Support, Air Force Logistics College, No. 85 Xige Street, Gulou District, Xuzhou, Jiangsu Province, China;1. College of Chemical and Biological Engineering, Zhejiang University, Hangzhou 310027, China;2. Department of Civil and Environmental Engineering and Department of Mechanical Engineering, Northwestern University, Evanston, IL 60208, USA;3. School of Aerospace Engineering and Applied Mechanics, Tongji University, Shanghai 200092, China |
| |
| Abstract: | The emergence of advanced computational methods and theoretical models for damage progression in composites has heralded the promise of virtual testing of composite structures with orthotropic lay-ups, complex geometries and multiple material systems. Recent studies have revealed that specimen size and material orthotropy has a major effect on the open hole tension (OHT) strength of composite laminates. The aim of this investigation is develop a progressive failure model for orthotropic composite laminates, employing stepwise discretization of the traction–separation relationship, to predict the effect of specimen size and laminate orthotropy on the OHT strength. The results show that a significant interaction exists between delamination and in-plane damage, so that models without considering delamination would over-predict strength. Furthermore, it is found that the increase in fracture toughness of blocked plies must be incorporated in the model to achieve good correlation with experimental results. |
| |
| Keywords: | C Damage mechanics C Computational modelling B Delamination B Damage tolerance |
| 本文献已被 ScienceDirect 等数据库收录！ |
|
