复合材料层合板面内渐进损伤分析的CDM模型

吴义韬; 姚卫星; 吴富强

doi:10.6052/0459-1879-13-106

复合材料层合板面内渐进损伤分析的CDM模型

doi: 10.6052/0459-1879-13-106

1.
飞行器先进设计技术国防重点学科实验室, 南京航空航天大学, 南京210016
2. 机械结构力学及控制国家重点实验室, 南京航空航天大学, 南京210016

基金项目: 国家自然科学基金（11202098）和江苏高校优势学科建设工程资助项目.

详细信息

作者简介:
姚卫星，教授，主要研究方向：飞行器综合设计和结构设计理论.E-mail：wxyao@nuaa.edu.cn

中图分类号: TB33
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出版历程
- 收稿日期: 2013-04-03
- 修回日期: 2013-07-01
- 刊出日期: 2014-01-18

CDM MODEL FOR INTRALAMINAR PROGRESSIVE DAMAGE ANALYSIS OF COMPOSITE LAMINATES

1.
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Funds: The project was supported by the National Natural Science Foundation of China(11202098) and the Priority Academic Program Development of Jiangsu Higher Education Institutions.

摘要

摘要: 基于连续介质损伤力学，提出了一个预测复合材料层合板面内渐进损伤分析的模型，它包括损伤表征、损伤判定和损伤演化3 部分. 模型能够区分纤维拉伸断裂、纤维压缩断裂、纤维间拉伸损伤和纤维间压缩损伤4 种损伤模式，定义了与4 个损伤模式对应的损伤状态变量，导出了材料主轴系下损伤前后材料本构之间的关系. 损伤起始采用Puck 准则判定，损伤演化由特征长度内应变能释放密度控制. 假定材料服从线性应变软化行为，建立了损伤状态变量关于断裂面上等效应变的渐进损伤演化法则. 模型涵盖了复合材料面内损伤起始、演化直至最终失效的全过程. 完成了含孔[45/0/-45/90]_2S 层合板在拉伸和压缩载荷下失效分析，结果表明该模型能合理进行层合板的强度预测和损伤失效分析.
- 复合材料层合板 /
- 材料本构 /
- 渐进损伤演化 /
- Puck准则
Abstract: Based on continuum damage mechanics (CDM), a model was proposed for predicting intralaminar progressive damage of composite laminates, including damage description, damage model judgment and damage evolution. Four different damage modes existent within lamina, namely, fiber tension fracture (FFT), fiber compression fracture (FFC), inter fiber tension fracture (IFFT) and inter fiber compression fracture (IFFC), were considered, and damage state variables corresponding to these four modes were also defined. Material constitutive relationship being in the damaged states in the material principal axes was derived compared to that of undamaged states. The onset of the damage was estimated with Puck's criteria and the evolution of the damage was controlled by the strain energy release density within the characteristic length. Assuming that the material was exhibited linear strain-softening behavior, a new damage evolution law associating damage state variables with equivalent strain on fracture plane was established in this paper. The proposed model can predict damage initiation, damage evolution and final failure of composite laminates. Failure analyses of [45/0/-45/90]_2S notched laminates under tension and compression were performed with the present model and showed that it is capable to predict the strength of the composite laminate and analyze the failure process.
- composite laminate /
- material constitutive relation /
- progressive damage evolution /
- puck criteria

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参考文献(34)

Marsh G. Airbus A350 XWB update. Reinforced Plastics, 2010, 54(6): 20-24

Mccartney LN. Prediction of ply crack formation and failure in laminates. Composites Science and Technology, 2002, 62(12-13): 1619-1631

Hashin Z. Finite thermoelastic fracture criterion with application to laminate cracking analysis. Journal of the Mechanics and Physics of Solids, 1996, 44(7): 1129-1145

Mccartney LN. Predicting transverse crack formation in cross-ply laminates. Composites Science and Technology, 1998, 58(7): 1069-1081

Chang KY, Llu S, Chang FK. Damage tolerance of laminated composites containing an open hole and subjected to tensile loadings. Journal of Composite Materials, 1991, 25: 274-301

Tserpes KI, Labeas G, Papanikos P, et al. Strength prediction of bolted joints in graphite/epoxy composite laminates. Composites Part B: Engineering, 2002, 33(7): 521-529 .

Zhao LG, Warrior NA, Long AC. Finite element modelling of damage progression in non-crimp fabric reinforced composites. Composites Science and Technology, 2006, 66(1): 36-50

王丹勇, 温卫东, 崔海涛. 含孔复合材料层合板静拉伸三维逐渐损伤分析. 力学学报, 2005, 37(6): 788-795 (Wang Danyong, Wen Weidong, Cui Haitao. Three-dimensional progressive damage analysis of omposite laminates containing a hole subjected to tensile loading. Chinese Journal of Theoretical and Applied Mechanics, 2005, 37(6): 788-795 (in Chinese))

徐焜, 许希武. 三维五向编织复合材料渐进损伤分析及强度预测. 固体力学学报, 2010, 31(2): 133-141 (Xu Kun, Xu Xiwu. Progressive damage analysis and strength prediction of 3D five-directional braided composites. Chinese Journal of Solid Mechanics, 2010, 31(2): 133-141 (in Chinese))

Puck A, Schürmann H. Failure analysis of FRP laminates by means of physically based phenomenological models. Composites Science and Technology, 2002, 62(12-13): 1633-1662

Edge EC. Stress-based Grant-Sanders method for predicting failure of composite laminates. Composites Science and Technology, 1998, 58(7): 1033-1041

Rotem A. Prediction of laminate failure with the ROTEM failure criterion. Composites Science and Technology, 1998, 58(7): 1083-1094

Matzenmiller A, Lubliner J, Taylor RL. A constitutive model for anisotropic damage in fiber-composites. Mechanics of Materials, 1995, 20(2): 125-152

Camanho P P, Maimí P, Dávila CG. Prediction of size effects in notched laminates using continuum damage mechanics. Composites Science and Technology, 2007, 67(13): 2715-2727

Maimí P, Camanho PP, Mayugo JA, et al. A continuum damage model for composite laminates: Part Ⅰ-Constitutive model. Mechanics of Materials, 2007, 39(10): 897-908

Lopes CS, Camanho PP, Gürdal Z, et al. Low-velocity impact damage on dispersed stacking sequence laminates. Part II: Numerical simulations. Composites Science and Technology, 2009, 69(7-8): 937-947

Lapczyk I, Hurtado JA. Progressive damage modeling in fiber-reinforced materials. Composites Part A: Applied Science and Manufacturing, 2007, 38(11): 2333-2341

Falzon BG, Apruzzese P. Numerical analysis of intralaminar failure mechanisms in composite structures. Part I: FE implementation. Composite Structures, 2011, 93(2): 1039-1046

Falzon BG, Apruzzese P. Numerical analysis of intralaminar failure mechanisms in composite structures. Part II: Applications. Composite Structures, 2011, 93(2): 1047-1053

Linde P, Pleitner J, de Boer H, et al. Modelling and simulation of fibre metal laminates. Boston Massachusetts: ABAQUS Inc, 2004.

姚辽军, 赵美英, 李沛城. 基于CDM的复合材料层合板插层补强强度分析. 西北工业大学学报, 2011, 29(5): 794-798 (Yao Liaojun, Zhao Meiying, Li Peicheng. Applying proved methods to reinforcement design of 3D CDM (continuum damage model) for notched composite laminate. Journal of Northwestern Polytechnical University, 2011, 29(5): 794-798 (in Chinese))

姚辽军, 赵美英, 万小朋. 基于CDM-CZM的复合材料补片补强参数分析. 航空学报, 2012, 33(4): 666-671 (Yao Liaojun, Zhao Meiying, Wan Xiaopeng. Parameter analysis of composite laminates with patched reinforcement based on CDM-CZM. Acta Aeronautica et Astronautica Sinica, 2012, 33(4): 666-671 (in Chinese))

李沛城, 姚辽军, 赵美英. 基于三维CDM的复合材料开口层合板失效分析. 机械科学与技术, 2013, 32(2): 305-308 (Li Peicheng, Yao Liaojun, Zhao Meiying. Failure analysis of notched composite laminate with 3d continuum damage mechanics. Mechanical Science and Technology for Aerospace Engineering, 2013, 32(2): 305-308 (in Chinese))

庞宝君, 陈勇, 郑伟等. Glass/Epoxy复合材料叠层板面内剪切连续损伤模型. 复合材料学报, 2013, 30(2): 201-208 (Pang Baojun, Chen Yong, Zheng Wei, et al. Continuum damage mechanics model of glass/epoxy composite laminate under in-plane shear loading. Acta Materiae Compositae Sinica, 2013, 30 (2): 201-208 (in Chinese))

方国东. 三维四向碳/环氧编织复合材料积累损伤及失效分析. [博士论文]. 哈尔滨: 哈尔滨工业大学, 2010. 57-62 (Fang Guodong. Progressive damage and failure analysis of 3D four-step Carbon/epoxy braided composites. [PhD Thesis]. Harbin: Harbin Institute of Technology, 2010. 57-62 (in Chinese))

Davila CG, Camanho PP, Rose CA. Failure criteria for FRP laminates. Journal of Composite Materials, 2005, 39(4): 323-345

Puck A, Kopp J, Knops M. Guidelines for the determination of the parameters in Puck's action plane strength criterion. Composites Science and Technology, 2002, 62(3): 371-378

Raghavan P, Ghosh S. A continuum damage mechanics model for unidirectional composites undergoing interfacial debonding. Mechanics of Materials, 2005, 37(9): 955-979

Hahn HT, Tsai SW. Nonlinear elastic behavior of unidirectional composite laminae. Journal of Composite Materials, 1973, 7: 102-118

Knops M. Analysis of Failure in Fiber Polymer Laminates: The Theory of Alfred Puck. Berlin, Germany: Springer, 2008

Puck A, Schürmann H. Failure analysis of FRP laminates by means of physically based phenomenological models. Composites Science and Technology, 1998, 58(7): 1045-1067

Wang J, Callus PJ, Bannister MK. Experimental and numerical investigation of the tension and compression strength of un-notched and notched quasi-isotropic laminates. Composite Structures, 2004, 64(3-4): 297-306

Soden PD, Hinton MJ, Kaddour AS. Lamina properties, lay-up configurations and loading conditions for a range of fibre-reinforced composite laminates. Composites Science and Technology, 1998, 58(7): 1011-1022

Mathews MJ, Swanson SR. Characterization of the interlaminar fracture toughness of a laminated carbon/epoxy composite. Composites Science and Technology, 2007, 67(7-8): 1489-1498

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