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Keywords: bending, failure criterion, finite element, glass fibre laminates, projectile, static perforation.

Summary

In aircraft and aerospace industries, composites manufactured from fibre reinforced epoxy resin are well recognized as promising materials for future applications because of their superior properties such as low density, high strength and stiffness, and good fatigue resistance. However, compared to aluminium alloys which are still the most widely used materials in aerospace industry nowadays, these composites have an obvious drawback in that they are sensitive to impact damage. To combine the beneficial properties of both metal alloys and composites, from the early 1980s, a new kind of material based on the concept of laminate, was developed gradually. The newly developed material, fibre metal laminates (FMLs), consisting of thin layers of metal sheet and unidirectional fibre layers imbedded in an adhesive system, ideally combines the advantages of these two components without sharing their individual disadvantages; therefore has excellent impact, fatigue and damage tolerance characteristics and a low density. During the last few decades, researchers have undertaken many experiments, theoretical analyses and numerical modelling to investigate and optimize the property and design of FMLs. Among this work, the failure behaviour of FMLs under static and impact loading has been, and still remains, a subject area of great concern for those interested in applying the materials to advanced industries. The failure behaviour of fibre under static and impact loading is more complex than that of metallic materials because there are many more factors that influence the growth of failure including the property of fibre material and matrix material, fibre orientation, fibre delamination, and applied stress and strain rate. It is therefore, important to have a failure model that can accurately predict the behaviour of fibre under static and impact loading.

In this paper, numerical models were developed to simulate the three-point bending behaviour of glass fibre laminated beams through quasi-static modelling using the finite element code ABAQUS/Explicit. The post failure phenomenon was simulated reasonably well. The numerical models were also developed to simulate static perforation of a projectile through glass fibre laminate panels using ABAQUS. The Hill potential criterion was used to model the laminates failure up to the peak loading. A series of three-point bending tests on 16-ply glass fibre laminated beams and static perforation tests on 4-ply, 8-ply and 16-ply glass fibre laminated panels were carried out to validate the corresponding computer models. The predicted load-displacement relationships and failure modes of the laminated beams and panels were compared with the experimentally obtained results. Reasonably good correlation was obtained.

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Front Page Browse CCP CSETS CTR IJRT Other Authors Search Purchase Guide FAQ Contact us	Civil-Comp Proceedings ISSN 1759-3433 CCP: 88 PROCEEDINGS OF THE NINTH INTERNATIONAL CONFERENCE ON COMPUTATIONAL STRUCTURES TECHNOLOGY Edited by: B.H.V. Topping and M. Papadrakakis Paper 313 Modelling Brittle Failure of Glass Fibre Composites Subjected to Static Loading J. Fan, Z.W. Guan and W.J. Cantwell Department of Engineering, University of Liverpool, United Kingdom doi:10.4203/ccp.88.313 purchase the full-text of this paper Full Bibliographic Reference for this paper J. Fan, Z.W. Guan, W.J. Cantwell, "Modelling Brittle Failure of Glass Fibre Composites Subjected to Static Loading", in B.H.V. Topping, M. Papadrakakis, (Editors), "Proceedings of the Ninth International Conference on Computational Structures Technology", Civil-Comp Press, Stirlingshire, UK, Paper 313, 2008. doi:10.4203/ccp.88.313 Keywords: bending, failure criterion, finite element, glass fibre laminates, projectile, static perforation. Summary In aircraft and aerospace industries, composites manufactured from fibre reinforced epoxy resin are well recognized as promising materials for future applications because of their superior properties such as low density, high strength and stiffness, and good fatigue resistance. However, compared to aluminium alloys which are still the most widely used materials in aerospace industry nowadays, these composites have an obvious drawback in that they are sensitive to impact damage. To combine the beneficial properties of both metal alloys and composites, from the early 1980s, a new kind of material based on the concept of laminate, was developed gradually. The newly developed material, fibre metal laminates (FMLs), consisting of thin layers of metal sheet and unidirectional fibre layers imbedded in an adhesive system, ideally combines the advantages of these two components without sharing their individual disadvantages; therefore has excellent impact, fatigue and damage tolerance characteristics and a low density. During the last few decades, researchers have undertaken many experiments, theoretical analyses and numerical modelling to investigate and optimize the property and design of FMLs. Among this work, the failure behaviour of FMLs under static and impact loading has been, and still remains, a subject area of great concern for those interested in applying the materials to advanced industries. The failure behaviour of fibre under static and impact loading is more complex than that of metallic materials because there are many more factors that influence the growth of failure including the property of fibre material and matrix material, fibre orientation, fibre delamination, and applied stress and strain rate. It is therefore, important to have a failure model that can accurately predict the behaviour of fibre under static and impact loading. In this paper, numerical models were developed to simulate the three-point bending behaviour of glass fibre laminated beams through quasi-static modelling using the finite element code ABAQUS/Explicit. The post failure phenomenon was simulated reasonably well. The numerical models were also developed to simulate static perforation of a projectile through glass fibre laminate panels using ABAQUS. The Hill potential criterion was used to model the laminates failure up to the peak loading. A series of three-point bending tests on 16-ply glass fibre laminated beams and static perforation tests on 4-ply, 8-ply and 16-ply glass fibre laminated panels were carried out to validate the corresponding computer models. The predicted load-displacement relationships and failure modes of the laminated beams and panels were compared with the experimentally obtained results. Reasonably good correlation was obtained. purchase the full-text of this paper (price £20) go to the previous paper go to the next paper return to the table of contents return to the book description purchase this book (price £145 +P&P)
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