碳纤维复材加筋壁板分层损伤扩展仿真分析
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- 英文论文题名：Simulation for Delamination Propagation of CFRP Stiffened Panel
- 论文作者：郭义林 ; 于春芳 ; 刘利阳
- 英文论文作者：Guo Yilin ; Yu Chunfang ; Liu Liyang ; Shenyang Aircraft Design & Research Institute
- 年：2016
- 作者机构：沈阳飞机设计研究所;
- 论文关键词：碳纤维复合材料 ; 分层损伤 ; 裂纹扩展 ; VCCT
- 英文论文关键词：CFRP ; delamination ; propagation ; VCCT
- 会议召开时间：2016-10-31
- 会议录名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）
- 英文会议录名称：Discovery,Innovation and Communication——Proceedings of 7th CSAA Science and Technology Youth Forum
- 语种：中文
- 分类号：TB33
- 学会代码：ZGHU
- 会议名称：探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛
- 会议地点：中国广东中山
- 主办单位：中国航空学会
- 学会名称：中国航空学会
- 页数：7
- 文件大小：3113k
- 原文格式：O
- 会议级别：全国
摘要
碳纤维复合材料广泛应用于飞机结构中,但在使用与维护过程中所造成的冲击损伤和几乎不可见损伤会造成灾难性后果,因此分析这些损伤显得尤为重要。分层损伤是复合材料的一种常见损伤,其在疲劳载荷和压缩载荷作用下易发生分层扩展。本文采用数值法,分析了具有分层损伤的碳纤维复合材料加筋板分层扩展和后屈曲承载能力.同时使用ABAQUS软件的虚拟裂纹闭合技术(VCCT),建立该模型,得出仿真分析结论。,本文的研究结果对于碳纤维复合材料损伤预测工作具有一定的参考价值。
CFRPs are widely used in aircraft,but they are sensitive to Low Velocity Impact(LVI) and Barely Visible Impact Damage(BVID) during service or maintenance which can lead to a catastrophe event.Delamination is a type of common damage which is sensitive to fatigue load and compressive load which can induce delamination growth.The thesis is uses the numerical analysis to analyze the delamination propagation and postbuckling load carrying ability of CFRP stiffened panel which has delamination damage.VCCT has been deployed in ABAQUS to simulate these models.The results concluded in this research can instruct perdictions of delamination propagation for CFRP structures.
CFRPs are widely used in aircraft,but they are sensitive to Low Velocity Impact(LVI) and Barely Visible Impact Damage(BVID) during service or maintenance which can lead to a catastrophe event.Delamination is a type of common damage which is sensitive to fatigue load and compressive load which can induce delamination growth.The thesis is uses the numerical analysis to analyze the delamination propagation and postbuckling load carrying ability of CFRP stiffened panel which has delamination damage.VCCT has been deployed in ABAQUS to simulate these models.The results concluded in this research can instruct perdictions of delamination propagation for CFRP structures.
引文
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[3]Krueger R.Computational Fracture Mechanics For Composites State of The Art and Challenges.Nafems Nordic Seminar:Prediction and Modelling of Failure Using FEA,Copenhagen/Roskilde,Denmark,2006.
[4]Sridharan S.Delamination Behaviour of Composites[M].Cambridge,Woodhead Publishing Limited,2008.
[5]Uda N,Ono K,Kunoo K.Compression Fatigue Failure of CFRP Laminates with Impact Damage[J].Composites Science and Teehnology,2009,69:2308-2314.
[6]Olsson R.Analytical Prediction of Large Mass Impact Damage in Composite Laminates[J].Composites Part A:Applied Science and Manufacturing,2001,32:1207-1215.
[7]Malhotra A,Guild F J.Impact Damage to Composite Laminates:Effect of Impact Location[J].Appl Compos Mater,2014,21:165-177.
[8]Yap J.Influence of Post-Buckling Behaviour of Composite Stiffened Panels on the Damage Criticality[J].Compos Struct,2004;66(1-4):197-206.
[9]Sridharan S.Delamination Behaviour of Composites[M].Cambridge,Woodhead Publishing Limited,2008.
[10]Krueger R.Fracture Mechanics for Composites State of the Art and Challenges.http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20080014103.pdf
[11]Reeder J R.A Bilinear Failure Criterion for Mixed-Mode Delamination,Composite Materials:Testing and Design.1993,11,ASTM STP 1206,Am Soc for Testing and Materials,Philadelphia,PA:303-322.
[2]Middleton D H,Composite Materials in Aircraft Structures[M].J Wiley,Longman Scientific&Technical,1990.
[3]Krueger R.Computational Fracture Mechanics For Composites State of The Art and Challenges.Nafems Nordic Seminar:Prediction and Modelling of Failure Using FEA,Copenhagen/Roskilde,Denmark,2006.
[4]Sridharan S.Delamination Behaviour of Composites[M].Cambridge,Woodhead Publishing Limited,2008.
[5]Uda N,Ono K,Kunoo K.Compression Fatigue Failure of CFRP Laminates with Impact Damage[J].Composites Science and Teehnology,2009,69:2308-2314.
[6]Olsson R.Analytical Prediction of Large Mass Impact Damage in Composite Laminates[J].Composites Part A:Applied Science and Manufacturing,2001,32:1207-1215.
[7]Malhotra A,Guild F J.Impact Damage to Composite Laminates:Effect of Impact Location[J].Appl Compos Mater,2014,21:165-177.
[8]Yap J.Influence of Post-Buckling Behaviour of Composite Stiffened Panels on the Damage Criticality[J].Compos Struct,2004;66(1-4):197-206.
[9]Sridharan S.Delamination Behaviour of Composites[M].Cambridge,Woodhead Publishing Limited,2008.
[10]Krueger R.Fracture Mechanics for Composites State of the Art and Challenges.http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20080014103.pdf
[11]Reeder J R.A Bilinear Failure Criterion for Mixed-Mode Delamination,Composite Materials:Testing and Design.1993,11,ASTM STP 1206,Am Soc for Testing and Materials,Philadelphia,PA:303-322.