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发展了层合复合材料面内及分层失效模型,模型考虑了横向压剪残余剪切变形和分层残余相对位移。提出一种块体单元包含若干铺层的模型,以减少复合材料逐层分析时的计算量。对一种碳纤/环氧层合复合材料进行了横向压痕试验,测量了不同压力下凹坑的深度,用超声C扫测得损伤面积。用发展的模型在ABAQUS平台上通过用户材料子程序UMAT模拟了上述试验,分析了试验曲线特征点对应的损伤机制,通过与试验结果的对比,验证了本文模型的合理性。
The in-plane and delamination failure models of laminated composites have been developed. The model considers the residual shear deformation of transverse compression shear and the residual relative displacement of stratification. In this paper, a model of a block unit containing several plies is proposed to reduce the computational complexity of layer-by-layer analysis of the composite material. A carbon fiber / epoxy laminate composite transverse indentation test, the depth of the depression was measured under different pressures, with C-scan ultrasonic damage area. The developed model is simulated on the ABAQUS platform by user material subroutine UMAT, and the damage mechanism corresponding to the characteristic points of the test curve is analyzed. The comparison with the test results proves the rationality of this model.