开孔玻璃纤维环氧树脂层压板的渐进疲劳建模

IF 3 Q2 MATERIALS SCIENCE, COMPOSITES
Victor Maneval, N. Vedvik, A. Echtermeyer
{"title":"开孔玻璃纤维环氧树脂层压板的渐进疲劳建模","authors":"Victor Maneval, N. Vedvik, A. Echtermeyer","doi":"10.3390/jcs7120516","DOIUrl":null,"url":null,"abstract":"The failure of composite laminates under cyclic fatigue loads is complex, as multiple failure mechanisms are in play at different scales and interact with each other. Predicting the remaining fatigue life as well as the residual capacities of a composite laminate or component is crucial, particularly for safety-critical applications. A progressive fatigue model is proposed to describe the catastrophic failure of open-hole laminates under tensile cyclic fatigue. To represent both intra-laminar and inter-laminar damage, a combination of a continuum damage mechanics model (CDM) and a discrete cohesive zone model (CZM) is implemented in the finite element (FE) software Abaqus. The CDM combines fibre- and matrix-dominated S-N curves with the Palmgren–Miner accumulation rule and Hashin’s residual strength to form a fatigue failure criterion differentiating between fibre failure (FF) and matrix failure (MF). The CZM implemented in this work is the CF20 model proposed by NASA. Fatigue cycling is simulated using an external cycle-jump scheme, where the stiffness degradation is conducted between the FE simulations outside of the implicit solver [90/0] s. Glass fibre reinforced polymer (GFRP) open-hole specimens were tested in tensile cyclic fatigue at a load ratio of 0.1. The experiments were reproduced numerically and the results compared. After calibration of a set of parameters based on one load level, the model was able to reproduce the experimental S-N curve very well, predicting a slope of −0.10, while the experimental value was −0.11. The failure sequence of the laminate was also successfully reproduced. The growth of the split from the hole, and its interaction with inter-laminar delamination, was successfully captured. The proposed approach was able to describe the fatigue failure of an open-hole laminate with a minimal set of material inputs using a simplified fatigue damage model while avoiding convergence issues.","PeriodicalId":15435,"journal":{"name":"Journal of Composites Science","volume":"33 4","pages":""},"PeriodicalIF":3.0000,"publicationDate":"2023-12-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Progressive Fatigue Modelling of Open-Hole Glass-Fibre Epoxy Laminates\",\"authors\":\"Victor Maneval, N. Vedvik, A. Echtermeyer\",\"doi\":\"10.3390/jcs7120516\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"The failure of composite laminates under cyclic fatigue loads is complex, as multiple failure mechanisms are in play at different scales and interact with each other. Predicting the remaining fatigue life as well as the residual capacities of a composite laminate or component is crucial, particularly for safety-critical applications. A progressive fatigue model is proposed to describe the catastrophic failure of open-hole laminates under tensile cyclic fatigue. To represent both intra-laminar and inter-laminar damage, a combination of a continuum damage mechanics model (CDM) and a discrete cohesive zone model (CZM) is implemented in the finite element (FE) software Abaqus. The CDM combines fibre- and matrix-dominated S-N curves with the Palmgren–Miner accumulation rule and Hashin’s residual strength to form a fatigue failure criterion differentiating between fibre failure (FF) and matrix failure (MF). The CZM implemented in this work is the CF20 model proposed by NASA. Fatigue cycling is simulated using an external cycle-jump scheme, where the stiffness degradation is conducted between the FE simulations outside of the implicit solver [90/0] s. Glass fibre reinforced polymer (GFRP) open-hole specimens were tested in tensile cyclic fatigue at a load ratio of 0.1. The experiments were reproduced numerically and the results compared. After calibration of a set of parameters based on one load level, the model was able to reproduce the experimental S-N curve very well, predicting a slope of −0.10, while the experimental value was −0.11. The failure sequence of the laminate was also successfully reproduced. The growth of the split from the hole, and its interaction with inter-laminar delamination, was successfully captured. The proposed approach was able to describe the fatigue failure of an open-hole laminate with a minimal set of material inputs using a simplified fatigue damage model while avoiding convergence issues.\",\"PeriodicalId\":15435,\"journal\":{\"name\":\"Journal of Composites Science\",\"volume\":\"33 4\",\"pages\":\"\"},\"PeriodicalIF\":3.0000,\"publicationDate\":\"2023-12-12\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Journal of Composites Science\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.3390/jcs7120516\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q2\",\"JCRName\":\"MATERIALS SCIENCE, COMPOSITES\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Journal of Composites Science","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.3390/jcs7120516","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q2","JCRName":"MATERIALS SCIENCE, COMPOSITES","Score":null,"Total":0}
引用次数: 0

摘要

复合材料层压板在循环疲劳载荷下的失效非常复杂,因为多种失效机制在不同尺度上发挥作用,并相互影响。预测复合材料层压板或组件的剩余疲劳寿命和剩余容量至关重要,尤其是对于安全关键型应用。本文提出了一种渐进疲劳模型,用于描述开孔层压板在拉伸循环疲劳下的灾难性失效。为了表示层内和层间损伤,在有限元(FE)软件 Abaqus 中结合使用了连续损伤力学模型(CDM)和离散内聚区模型(CZM)。CDM 将纤维和基体主导的 S-N 曲线与 Palmgren-Miner 积累规则和 Hashin 残余强度相结合,形成了区分纤维破坏 (FF) 和基体破坏 (MF) 的疲劳破坏标准。本研究采用的 CZM 是美国国家航空航天局提出的 CF20 模型。疲劳循环使用外部循环跳转方案进行模拟,其中刚度退化在隐式求解器 [90/0] s 之外的 FE 模拟之间进行。玻璃纤维增强聚合物(GFRP)开孔试样在 0.1 负载比下进行拉伸循环疲劳测试。对实验进行了数值模拟,并对结果进行了比较。根据一个载荷水平校准一组参数后,模型能够很好地再现实验 S-N 曲线,预测斜率为 -0.10,而实验值为 -0.11。层压板的破坏顺序也被成功再现。模型成功捕捉到了孔洞裂缝的增长及其与层间分层的相互作用。所提出的方法使用简化的疲劳损伤模型,以最小的材料输入集描述了开孔层压板的疲劳破坏,同时避免了收敛问题。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Progressive Fatigue Modelling of Open-Hole Glass-Fibre Epoxy Laminates
The failure of composite laminates under cyclic fatigue loads is complex, as multiple failure mechanisms are in play at different scales and interact with each other. Predicting the remaining fatigue life as well as the residual capacities of a composite laminate or component is crucial, particularly for safety-critical applications. A progressive fatigue model is proposed to describe the catastrophic failure of open-hole laminates under tensile cyclic fatigue. To represent both intra-laminar and inter-laminar damage, a combination of a continuum damage mechanics model (CDM) and a discrete cohesive zone model (CZM) is implemented in the finite element (FE) software Abaqus. The CDM combines fibre- and matrix-dominated S-N curves with the Palmgren–Miner accumulation rule and Hashin’s residual strength to form a fatigue failure criterion differentiating between fibre failure (FF) and matrix failure (MF). The CZM implemented in this work is the CF20 model proposed by NASA. Fatigue cycling is simulated using an external cycle-jump scheme, where the stiffness degradation is conducted between the FE simulations outside of the implicit solver [90/0] s. Glass fibre reinforced polymer (GFRP) open-hole specimens were tested in tensile cyclic fatigue at a load ratio of 0.1. The experiments were reproduced numerically and the results compared. After calibration of a set of parameters based on one load level, the model was able to reproduce the experimental S-N curve very well, predicting a slope of −0.10, while the experimental value was −0.11. The failure sequence of the laminate was also successfully reproduced. The growth of the split from the hole, and its interaction with inter-laminar delamination, was successfully captured. The proposed approach was able to describe the fatigue failure of an open-hole laminate with a minimal set of material inputs using a simplified fatigue damage model while avoiding convergence issues.
求助全文
通过发布文献求助,成功后即可免费获取论文全文。 去求助
来源期刊
Journal of Composites Science
Journal of Composites Science MATERIALS SCIENCE, COMPOSITES-
CiteScore
5.00
自引率
9.10%
发文量
328
审稿时长
11 weeks
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
确定
请完成安全验证×
copy
已复制链接
快去分享给好友吧!
我知道了
右上角分享
点击右上角分享
0
联系我们:info@booksci.cn Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。 Copyright © 2023 布克学术 All rights reserved.
京ICP备2023020795号-1
ghs 京公网安备 11010802042870号
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术官方微信