纤维复合材料层合板在四点弯曲载荷下的损伤分析

摘要/Abstract

摘要： 实验测试了T300/7901碳纤维复合材料_8s层合板在四点弯曲静载下的载荷-位移响应及破坏载荷。基于桥联模型,在商用软件Abaqus/CAE中实现对该层合板在四点弯曲静载条件下的层内以及层间损伤破坏进行模拟分析。分析方法分为四个部分:仅利用组分材料数据,基于桥联模型对单向复合材料层的本构关系建模;利用考虑三维应力的Hashin判据预报复合材料层的纤维拉伸、压缩损伤及基体拉伸、压缩损伤;出现组分材料损伤后对相应材料点采用Camando方法进行刚度退化;在复合材料单层中间插入薄的纯树脂层,通过树脂层的损伤破坏分析层间分层。在Abaqus/Explicit模块中,利用子程序VUMAT完成以上材料建模分析;将模拟结果与实验数据进行对比。结果表明,模拟得到的载荷-位移曲线及破坏载荷与实验结果吻合很好,所提出的材料模型能有效预报纤维复合材料层合板的层内及层间损伤破坏情况。

关键词: 纤维复合材料层合板, 四点弯曲, 层间树脂层, 渐进损伤模型

Abstract: In this paper, the load-displacement response and fracture strength of _8s T300/7901 carbon fiber/epoxy composite laminate under four-point bending were investigated both experimentally and theoretically. The intra and inter layer damages of the laminate under four-point bending load were analyzed using commercial software Abaqus/CAE incorporated with micromechanical Bridging Model. The analysis scheme is implemented into a user-subroutine VUMAT, which requires input of only the constituent fiber and matrix material data. The constitutive relationship of a unidirectional lamina layer is defined using Bridging Model, and 3D Hashin′s criterion is applied to detect a fiber tensile/compressive or matrix tensile/compressive induced failure of the layer. Once a constituent failure occurs, the Camando′s method is used to degrade its elastic modulus. A thin pure matrix layer is inserted in between two adjacent lamina layers, and an interlayer de-cohesive failure is assumed when the matrix layer′s damage is attained. The simulation results are compared with our experimental data. The results show that the simulated load-displacement curve and ultimate strength agree well with the measured results. The proposed model is capable of predicting the intra- and inter-layer damages of a laminated composite.

Key words: composite laminate, four-point bending, matrix interlayer, progressive damage analysis

中图分类号:

TB332

赵玉卿, 姜峰, 黄争鸣. 纤维复合材料层合板在四点弯曲载荷下的损伤分析[J]. 复合材料科学与工程, 2020, 0(2): 10-18.

ZHAO Yu-qing, JIANG Feng, HUANG Zheng-ming. DAMAGE ANALYSIS OF FIBER COMPOSITE LAMINATES UNDERFOUR POINT BENDING LOAD[J]. Composites Science and Engineering, 2020, 0(2): 10-18.

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