国产碳纤维复合材料开孔拉伸失效分析与预测

肖梦丽; 张勇波; 王治华; 傅惠民; 杨鑫

doi:10.13224/j.cnki.jasp.2015.12.006

国产碳纤维复合材料开孔拉伸失效分析与预测

doi: 10.13224/j.cnki.jasp.2015.12.006

北京航空航天大学小样本技术研究中心, 北京 100191

基金项目:

国家自然科学基金(11501022)

北京市自然科学基金(3154034)

详细信息

作者简介:
肖梦丽(1990-),女,湖北麻城人,硕士生,从事复合材料力学与失效分析研究.

中图分类号: V258;O211
计量
- 文章访问数: 1171
- HTML浏览量: 158
- PDF量: 548
- 被引次数: 0
出版历程
- 收稿日期: 2014-05-05
- 刊出日期: 2015-12-28

Failure analysis and prediction on the open-hole tensionof domestic carbon fiber composite

Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 基于国产碳纤维复合材料含孔层合板失效模式和损伤机理研究,结合试验分析建立了符合其失效机理的有限元模型,并在有限元模型中研究了不同失效准则对剩余强度计算结果的影响,通过比较试验数据与数值模拟结果表明:二维模型能比较准确地预测国产碳纤维复合材料含孔层合板的剩余强度,破坏载荷的数值模拟与试验数据的相对误差为7.9%,而拉伸模量的相对误差为5.6%.
- 复合材料层合板 /
- 拉伸试验 /
- 渐进失效分析 /
- 有限元法 /
- 剩余强度
Abstract: Based on the research of the failure mode and damage mechanism of the notched domestic carbon fiber composite laminates and the experimental analysis, finite element models were established. Then the effect of different failure criterias on the residual strength of notcked domestic carbor fiber composite laminates was studied in the corresponding finite element model. Through the comparison between experimental data and simulation results, it was found that the two-dimensional model could predict the residual strength of the notched domestic carbon fiber composite laminates accurately, the relative error between numerical simulation result and experimental data of failure load was 7.9%,while the relative error of tensile modulus was 5.6%.
- composite laminates /
- tension experiment /
- progressive failure analysis /
- finite element method /
- residual strength

HTML

参考文献(18)

[1]	何文治,陈绍杰.复合材料设计手册[M].北京:航空工业出版社,1990.
[2]	崔海涛,赫勇,温卫东.含孔复合材料层合板逐渐损伤破坏分析[J].理化检验:物理分册,2002,38(4):150-153. CUI Haitao,HAO Yong,WEN Weidong.Accumulative damage and failure analysis of laminated composites with hole[J].Physical Testing and Chemical Analysis:Part A Physical Testing,2002,38(4):150-153.(in Chinese)
[3]	黎增山,关志东,何为,等.复合材料开孔拉伸损伤分析[J].复合材料学报,2012,29(1):169-175. LI Zengshan,GUAN Zhidong,HE Wei,et al.Damage analysis of open-hole tension laminates[J].Acta Materiae Compositae Sinica,2012,29(1):169-175.(in Chinese)
[4]	Chang K Y,LIU Sheng,Chang F K.Damage tolerance of laminated composites containing an open hole and subjected to tensile loadings[J].Journal of Composite Materials,1991,25(3):274-301.
[5]	Maa R H,Cheng J H.A CDM-based failure model for predicting strength of notched composite laminates[J].Composites:Part B Engineering,2002,33(6):479-489.
[6]	Ridha M,Wang C H,Chen B Y,et al.Modelling complex progressive failure in notched composite laminates with varying sizes and stacking sequences[J].Composites:Part A Applied Science and Manufacturing,2014,58(3):16-23.
[7]	Kostopoulos V,Pappas Y Z.Notched strength prediction of centre-hole carbon/carbon composites[J].Materials Science and Engineering:A,1998,250(2):320-327.
[8]	Matrin-Santos E,Maini P,Gonzalez E V,et al.A continuum constitutive model for the simulation of fabric-reinforced composites[J].Composite Structures,2014,111(11):122-129.
[9]	Morais A B D.Open-hole tensile strength of quasi-isotropic laminates[J].Composites Science and Technology,2000,60(10):1997-2004.
[10]	韩小平,郭章新,朱西平,等.含孔复合材料层合板孔边的应力集中[J].复合材料学报,2009,26(1):168-173. HAN Xiaoping,GUO Zhangxin,ZHU Xiping,et al.Stress distribution near the opening and stress concentration for composite laminates with circular opening[J].Acta Materiae Compositae Sinica,2009,26(1):168-173.(in Chinese)
[11]	傅惠民,杨雨松,张勇波.国产碳纤维CCF300与T300碳纤维复合材料拉伸载荷下的失效模式分析[J].航空动力学报,2010,25(10):2163-2169. FU Huimin,YANG Yusong,ZHANG Yongbo.Failure mode research on CCF300 and T300 composite laminates under tensile strength[J].Journal of Aerospace Power,2010,25(10):2163-2169.(in Chinese)
[12]	傅惠民,杨雨松,张勇波.含分层损伤国产碳纤维CCF300与T300碳纤维复合材料层合板压缩失效模式[J].航空动力学报,2011,26(11):2416-2421. FU Huimin,YANG Yusong,ZHANG Yongbo.Failure mode research on CCF300 and T300 carbon fiber composite laminates with delamination under compressive strength[J].Journal of Aerospace Power,2011,26(11):2416-2421.(in Chinese)
[13]	彭文杰.复合材料层合结构极限强度预测方法及分层应力最小化研究[D].武汉:华中科技大学,2009. PENG Wenjie.Study on the ultimate strength of laminated composites and the minimization of delamination stresses[D].Wuhan:Huazhong University of Science and Technology.(in Chinese)
[14]	Kuo S Y,Shiau L C,Chen K H.Buckling analysis of shape memory alloy reinforced composite laminates[J].Composite Structures,2009,90(2):188-195.
[15]	唐文勇,陈念众,张圣坤.复合材料加筋层合板的极限强度分析[J].工程力学,2007,24(8):43-48. TANG Wenyong,CHEN Nianzhong,ZHANG Shengkun.Ultimate strength analysis of stiffend laminated plates[J].Engineering Mechanics,2007,24(8):43-48.(in Chinese)
[16]	HAN Wanmin,Petyt M.Linear vibration analysis of laminated rectangular plates using the hierarchical finite element method[J].Computers and Structures,1996,61(4):706-712.
[17]	Hashin Z.Failure criteria for unidirectional fiber composites[J].Journal of Applied Mechanics,1980,47(2):329-334.
[18]	Tserpes K I,Labeas G.Strength prediction of bolted joints in graphite/epoxy composite laminates[J].Composites:Part B Engineering,2002,33(10):521-529.