It is of engineering significance to determine the parameters of reinforcement design of notched composite laminates. In order to understand the influence of these parameters on the structure strength and damage propagation, a three-dimension anisotropic continuum damage model (CDM) is developed to describe the onset and damage evolution in a notched composite laminate under tensile loading condition. A cohesive zone model (CZM) is used to simulate the damage evolution of an adhesive material between the notched composite laminate and the patched reinforcement structure. Good agreement is obtained between the numerical and the experimental results. Based on the validated model, three main parameters for reinforcement design are discussed, i.e., the lay-up configuration, patch thickness and radius of patch reinforcement. Furthermore, the delamination of the adhesive layer between the laminate and the patch is found to be the primary reason for the final failure of the reinforced structure.
YAO Liaojun
,
ZHAO Meiying
,
WAN Xiaopeng
. Parameter Analysis of Composite Laminates with Patched Reinforcement Based on CDM-CZM[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012
, (4)
: 666
-671
.
DOI: CNKI:11-1929/V.20111011.1411.007
[1] Matzenmiller A, Lubliner J, Taylor R L. A constitutive model for anisotropic damage in fiber-composites. Mechanics of Material, 1995, 20(2): 125-152.
[2] Maimi P, Camanho P P, Mayugo J A, et al. A continuum damage model for composite laminates: Part I—constitutive model. Mechanics of Materials, 2007, 39(10): 896-908.
[3] Maimi P, Camanho P P, Mayugo J A, et al. A continuum damage model for composite laminates: Part II—computational implementation and validation. Mechanics of Materials, 2007, 39(10): 909-919.
[4] Maimi P, Camanho P P, Davila C G. Prediction of size effects in notched laminates using continuum damage mechanics. Composites Science and Technology, 2007, 67(13): 2715-2727.
[5] Lopes C S, Seresta O, Coquet Y, et al. Low-velocity impact damage on dispersed stacking sequence laminates: Part I—experiments. Composites Science and Technology, 2009, 69(7-8): 926-936.
[6] Lopes C S, Camanho P P, Gurdal 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.
[7] Qing H, Mishnaevsky L. 3D constitutive model of anisotropic damage for unidirectional ply based on physical failure mechanisms. Computational Materials Science, 2010, 50(2): 479-486.
[8] Linde P, Pleitner J, Henk D B, et al. Modelling and simulation of fibre metal laminates. 2004 ABAQUS Users’ Conference. Boston Massachusetts: ABAQUS Inc. 2004: 412-439.
[9] Lemaitre J, Desmorat R. Engineering damage mechanics: ductile, creep, fatigue and brittle failure. Berlin, Heidelberg: Springer, 2010.
[10] Lapczyk I, Hurtado J A. Progressive damage modeling in fiber-reinforced materials. Composites Part A: Applied Science and Manufacturing, 2007, 38(11): 2333-2341.
[11] Huang C H, Lee Y J. Experiments and simulation of the static contact crush of composite laminated plates. Composite Structures, 2003, 61(3): 265-270.
[12] Cui H, Li Y L, Liu Y Y, et al. Numerical simulation of composites joints failure based on cohesive zone model. Acta Materiae Compositae Sinica, 2010, 27(2): 161-168. (in Chinese) 崔浩, 李玉龙, 刘元镛, 等. 基于粘聚区模型的含填充区复合材料接头失效数值模拟. 复合材料学报, 2010, 27(2): 161-168.
[13] Camanho P P, Davila C G. Mixed-mode decohesion finite elements for the simulation of delamination in composite material. NASA/TM-2002-211737, 2002.
[14] Kou C H, Wang T, Li Z N, et al. Reinforcement research of composite laminates containing a circle hole. Journal of Beijing University of Aeronautics and Astronautics,1997, 23(4): 477-481. (in Chinese) 寇长河,汪彤, 郦正能, 等. 复合材料层合板开口补强研究. 北京航空航天大学学报,1997, 23(4): 477-481.
[15] Zhao Q S. Evaluation of the toughness of QY8911 bismaleimde. Acta Aeronautica et Astronautica Sinica,1991, 12(1): 41-46.(in Chinese) 赵渠森. QY8911双马来酰亚胺树脂韧性评定. 航空学报, 1991, 12(1): 41-46.
CJA