复合材料ENF试件裂纹扩展理论分析

doi:10.7527/S1000-6893.2013.0297

固体力学与飞行器总体设计

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复合材料ENF试件裂纹扩展理论分析

刘伟先, 周光明, 王新峰

南京航空航天大学机械结构力学与控制国家重点试验室, 江苏南京 210016

收稿日期:2013-04-01 修回日期:2013-05-30 出版日期:2014-01-25 发布日期:2013-07-01
通讯作者: 周光明，Tel.：025-84892546 E-mail：zhougm@nuaa.edu.cn E-mail:zhougm@nuaa.edu.cn
作者简介:刘伟先男，博士研究生。主要研究方向：复合材料损伤模型、损伤参数识别及其在复合材料修理中的运用。Tel：025-84896353 E-mail：liuweixian1986@gmail.co；周光明男，博士，教授，博士生导师。主要研究方向：先进复合材料结构设计、分析和工程问题的计算机建模与仿真。Tel：025-84892564 E-mail：zhougm@nuaa.edu.cn
基金资助:
江苏高校优势学科建设工程资助项目

Theoretical Analysis of Crack Propagation in Composite ENF Specimens

LIU Weixian, ZHOU Guangming, WANG Xinfeng

State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2013-04-01 Revised:2013-05-30 Online:2014-01-25 Published:2013-07-01
Supported by:
Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要：

对复合材料端部缺口弯曲（ENF）试件裂纹扩展过程进行了理论分析，研究了界面参数变化对载荷-位移曲线的影响。首先在梁微段分析的基础上，通过双线性Cohesive本构模型模拟了界面损伤。本文模型中考虑了轴力的影响，根据界面损伤程度对模型进行了分段，并分别获得了各段通解。以裂纹长度以及黏聚区范围为变量分析了ENF试件裂纹扩展过程，求解获得了载荷-位移曲线。通过与已有理论模型结果对比，验证了本文理论分析的正确性，且本文理论考虑了弹性段后非线性的存在。分析了界面参数与黏聚区长度的关系，为界面参数的选取提供了一定的依据。

关键词: ENF试件, Cohesive理论, 轴力影响, 裂纹扩展, 黏聚区长度

Abstract:

A theoretical analysis of crack propagation in end notch flexure (ENF) specimens is carried out, and the influence of the interface parameters on its load-displacement curve is investigated. Based on the micro analysis of a beam, the interface damage is simulated using a bilinear cohesive constitutive model. In this paper the influence of the axial force is taken into account. The model is segmented according to the degree of interface damage, and a general solution of each segment of the ENF specimen is obtained. The crack length and the cohesive zone range are taken as variables to analyze the ENF specimen crack propagation process and obtain the load-displacement curve. To verify this theoretical analysis when the nonlinear phenomenon after elastic deformation is considered, some comparisons are made with the existing theoretical results. The relationship between the interface parameters and the cohesive zone length is investigated. These results provide a basis for the selection of interface parameters.

Key words: ENF specimen, cohesive theory, effect of axial force, crack propagation, cohesive zone length

中图分类号:

V21
TB332

刘伟先, 周光明, 王新峰. 复合材料ENF试件裂纹扩展理论分析[J]. 航空学报, 2014, 35(1): 187-194.

LIU Weixian, ZHOU Guangming, WANG Xinfeng. Theoretical Analysis of Crack Propagation in Composite ENF Specimens[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(1): 187-194.

参考文献

[1] Russell A J, Street K N. Factors affecting the interlaminar fracture energy of graphite/epoxy laminates[C]//Progress in Science and Engineering of Composites:Proceedings of the Fourth International Conference on Composite Materials, 1982: 279-286.

[2] Carlsson L A, Gillespie J W, Jr, Pipes R B. On the analysis and design of the end notched flexure (ENF) specimen for Mode Ⅱ testing[J]. Journal of Composite Materials, 1986, 20(6): 594-604.

[3] Whitney J M, Gillespie J W, Jr, Carlsson L. Singularity approach to the analysis of the end notch flexure specimen.(retroactive coverage)[C]//American Society for Composites Second Technical Conference, 1987: 391-398.

[4] Whitney J M. Analysis of interlaminar Mode Ⅱ bending specimens using a higher order beam theory[J]. Journal of Reinforced Plastics and Composites, 1990, 9(6): 522-536.

[5] Wang Y, Williams J G. Corrections for Mode Ⅱ fracture toughness specimens of composites materials[J]. Composites Science and Technology, 1992, 43(3): 251-256.

[6] Chatterjee S N. Analysis of test specimens for interlaminar Mode Ⅱ fracture toughness, Part 1: elastic laminates[J]. Journal of Composite Materials, 1991, 25(5): 470-493.

[7] Corleto C R, Hogan H A. Energy release rates for the ENF specimen using a beam on an elastic foundation[J]. Journal of Composite Materials, 1995, 29(11): 1420-1436.

[8] Ozdil F, Carlsson L A, Davies P. Beam analysis of angle-ply laminate end-notched flexure specimens[J]. Composites Science and Technology, 1998, 58(12): 1929-1938.

[9] Ding W, Kortschot M T. A simplified beam analysis of the end notched flexure Mode Ⅱ delamination specimen[J]. Composite Structures, 1999, 45(4): 271-278.

[10] Wang J, Qiao P. Novel beam analysis of end notched flexure specimen for Mode-Ⅱ fracture[J]. Engineering Fracture Mechanics, 2004, 71(2): 219-231.

[11] De Morais A B. Novel cohesive beam model for the end-notched flexure (ENF) specimen[J]. Engineering Fracture Mechanics, 2011, 78(17): 3017-3029.

[12] Raghu Prasad B K, Pavan Kumar D. Analysis of composite ENF specimen using higher order beam theories[J]. Thin-Walled Structures, 2008, 46(6): 676-688.

[13] Chen Y, Qiao P Z. Cohesive analytic model of 4ENF specimen[J]. Journal of Hohai University: Natural Sciences, 2008, 36(2): 234-237. (in Chinese) 陈瑛, 乔丕忠. 4ENF 黏聚解析模型分析[J]. 河海大学学报: 自然科学版, 2008, 36(2): 234-237.

E-mail：hkxb@buaa.edu.cn

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复合材料ENF试件裂纹扩展理论分析

Theoretical Analysis of Crack Propagation in Composite ENF Specimens

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