Z-pin增强复合材料结构研究综述
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- 英文论文题名：Review of the Study on Z-pin Reinforced Composite Structures
- 论文作者：朱洪艳 ; 南力强 ; 云庆文 ; 王珺
- 英文论文作者：Zhu Hongyan ; Nan Liqiang ; Yun Qingwen ; Wang Jun ; Aircraft Design & Research Institute of AVIC Harbin Aircraft Industry Group CO.LTD.
- 年：2016
- 作者机构：中航工业哈尔滨飞机工业集团有限责任公司飞机设计研究所;
- 论文关键词：航空 ; 复合材料结构 ; 层压板 ; Z-pin
- 英文论文关键词：aircraft ; composite structure ; laminate ; Z-pin
- 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（上册）
- 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：V214.8
- 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：6
- 文件大小：1020k
- 原文格式：O
- 会议级别：全国
摘要
Z-pin一般是直径很小的碳纤维杆,它被插入到复合材料层压板或接头厚度方向内,以便提高它们的层间性能。Z-pin增强技术在通过大量的试验验证后已被成功地应用到了一些航空复合材料结构上,但应用有限。本文综述了Z-pin复合材料的概念、制造方法以及Z-pin增强对复合材料层压板性能的影响,并对其未来发展方向做了展望。
Z-pins are commonly small diameter carbon rods.They are inserted through the thickness of composite laminates and joints to improve their interlaminar properties.Z-pin reinforcement technology has been successfully used in some composite aircraft structures through extensive experimental certification test,but its application is a limited number.The concept and manufacture methods of Z-pin reinforced composite laminates,and the effect of Z-pin reinforcement on properties of composite laminates are reviewed in the paper,and its development direction is prospected in the future.
Z-pins are commonly small diameter carbon rods.They are inserted through the thickness of composite laminates and joints to improve their interlaminar properties.Z-pin reinforcement technology has been successfully used in some composite aircraft structures through extensive experimental certification test,but its application is a limited number.The concept and manufacture methods of Z-pin reinforced composite laminates,and the effect of Z-pin reinforcement on properties of composite laminates are reviewed in the paper,and its development direction is prospected in the future.
引文
[1]Schlueter A M.An Experimental Study of Rate Effects on Mode I Delamination of Z-pinned Composite Laminates[D].Ph.D.Dissertation,Purdue University,2012.
[2]Frietas G,Magee C,Dardzinski P,et al.Fiber Insertion Process for Improved Damage Tolerance in Aircraft laminates[J].Journal of Advanced Materials.1994,25:36-43.
[3]Choi I H,Kim I G,Ahn S M,et al.New Manufacturing Method of Z-pinned Composite Laminates[C].AIAA,2010-3133,2010.
[4]Partridge I K,Cartie D D R,Bonnington T.Manufacture and Performance of Z-Pinned Composites[J].Advanced Polymeric Materials.2003:103-138.
[5]Dickinson L C,Farley G L,Hinders M K.Prediction of Effective Three Dimensional Elastic Constants of Translaminar Reinforced Composite-s[J].Journal of Composite Materials,1999,33:1002-1029.
[6]Grassi M,Zhang X,Meo M.Prediction of Stiffness and Stresses in Z-Fibre Reinforced Composite Laminates[J].Composites Part A:Applied Science and Manufacturing,2002,33:1653-1664.
[7]Mouritz A P.Review of Z-Pinned Composite Laminates[J].Composites Part A:Applied Science and Manufacturing,2007,38:2383-2397.
[8]Partridge I K,Cartie D D R,Troulis M,et al.Evaluating the Mechanical Effectiveness of Z-Pinning[C].Materials and Processing:35th International SAMPE Technical Conference,2003.
[9]Steeves C A,Fleck N.In-Plane properties of Composite Laminates with Through-Thickness Pin Reinforcement[J].International Journal of Solids and Structures,2006,43:3197-3212.
[10]Steeves C A,Fleck N A.In-Plane Properties of CFRP Laminates Containing through Thickness Reinforcing Rods(Z-pins)[C].Procs.ICCM12,Paris,eds.Massard T.and Vautrin A,1999.
[11]Chang P,Mouritz A P,Cox B N.Flexural Properties of Z-Pinned Laminates[J].Composites Part A:Applied Science and Manufacturing,2007,38;244-251.
[12]Mouritz A P.Compression Properties of Z-Pinned Composite Laminates[J].Composites Science and Technology,2007,67:3110-3120.
[13]Chang P,Mouritz A,Cox B.Properties and Failure Mechanisms of Pinned Composite Lap Joints in Monotonic and Cyclic Tension[J].Composites Science and Technology,2006,66:2163-2176.
[14]Chang P,Mouritz A P,Cox B N.Properties and Failure Mechanisms of Z-Pinned Laminates in Monotonic and Cyclic Tension[J].Composites Part A:Applied Science and Manufacturing,2006,37;1501-1513.
[15]Partridge I K,Carrie D D R.Delamination Resistant Laminates by Z-Fiber Pinning:Part I Manufacture and Fracture Performance[J].Composites Part A:Applied Science and Manufacturing,2005,36;55-64.
[16]Carti6 DDR,Troulis M,Partridge I K.Delaminalion of Zpinned Carbon Fibre Reinforced Laminates[J].Composites Science and Technology,2006,66:855-861.
[17]Rugg K L,Cox B N,Massabd R.Mixed Mode Delamination of Polymer Composite Laminates Reinforced through the Thickness by Z-Fibers[J].Composites Part A:Applied Science and Manufacturing,2002,33;177-190.
[18]Pegorin F,Pingkarawat K,Daynes S,et al.Influence of Z-Pin Length on the Delamination Fracture Toughness and Fatigue Resistance of Pinned Composites[J].Composites Part B,2015,78:298-307.
[19]Huang H S,Waas A M.Quasi-Static Mode II Fracture Tests and Simulations of Z-Pinned Woven Composites[J].Engineering Fracture Mechanics,2014,126:155-165.
[2]Frietas G,Magee C,Dardzinski P,et al.Fiber Insertion Process for Improved Damage Tolerance in Aircraft laminates[J].Journal of Advanced Materials.1994,25:36-43.
[3]Choi I H,Kim I G,Ahn S M,et al.New Manufacturing Method of Z-pinned Composite Laminates[C].AIAA,2010-3133,2010.
[4]Partridge I K,Cartie D D R,Bonnington T.Manufacture and Performance of Z-Pinned Composites[J].Advanced Polymeric Materials.2003:103-138.
[5]Dickinson L C,Farley G L,Hinders M K.Prediction of Effective Three Dimensional Elastic Constants of Translaminar Reinforced Composite-s[J].Journal of Composite Materials,1999,33:1002-1029.
[6]Grassi M,Zhang X,Meo M.Prediction of Stiffness and Stresses in Z-Fibre Reinforced Composite Laminates[J].Composites Part A:Applied Science and Manufacturing,2002,33:1653-1664.
[7]Mouritz A P.Review of Z-Pinned Composite Laminates[J].Composites Part A:Applied Science and Manufacturing,2007,38:2383-2397.
[8]Partridge I K,Cartie D D R,Troulis M,et al.Evaluating the Mechanical Effectiveness of Z-Pinning[C].Materials and Processing:35th International SAMPE Technical Conference,2003.
[9]Steeves C A,Fleck N.In-Plane properties of Composite Laminates with Through-Thickness Pin Reinforcement[J].International Journal of Solids and Structures,2006,43:3197-3212.
[10]Steeves C A,Fleck N A.In-Plane Properties of CFRP Laminates Containing through Thickness Reinforcing Rods(Z-pins)[C].Procs.ICCM12,Paris,eds.Massard T.and Vautrin A,1999.
[11]Chang P,Mouritz A P,Cox B N.Flexural Properties of Z-Pinned Laminates[J].Composites Part A:Applied Science and Manufacturing,2007,38;244-251.
[12]Mouritz A P.Compression Properties of Z-Pinned Composite Laminates[J].Composites Science and Technology,2007,67:3110-3120.
[13]Chang P,Mouritz A,Cox B.Properties and Failure Mechanisms of Pinned Composite Lap Joints in Monotonic and Cyclic Tension[J].Composites Science and Technology,2006,66:2163-2176.
[14]Chang P,Mouritz A P,Cox B N.Properties and Failure Mechanisms of Z-Pinned Laminates in Monotonic and Cyclic Tension[J].Composites Part A:Applied Science and Manufacturing,2006,37;1501-1513.
[15]Partridge I K,Carrie D D R.Delamination Resistant Laminates by Z-Fiber Pinning:Part I Manufacture and Fracture Performance[J].Composites Part A:Applied Science and Manufacturing,2005,36;55-64.
[16]Carti6 DDR,Troulis M,Partridge I K.Delaminalion of Zpinned Carbon Fibre Reinforced Laminates[J].Composites Science and Technology,2006,66:855-861.
[17]Rugg K L,Cox B N,Massabd R.Mixed Mode Delamination of Polymer Composite Laminates Reinforced through the Thickness by Z-Fibers[J].Composites Part A:Applied Science and Manufacturing,2002,33;177-190.
[18]Pegorin F,Pingkarawat K,Daynes S,et al.Influence of Z-Pin Length on the Delamination Fracture Toughness and Fatigue Resistance of Pinned Composites[J].Composites Part B,2015,78:298-307.
[19]Huang H S,Waas A M.Quasi-Static Mode II Fracture Tests and Simulations of Z-Pinned Woven Composites[J].Engineering Fracture Mechanics,2014,126:155-165.