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提出了一种分析和预测在压缩载荷作用下纤维增强复合材料机翼长桁的极限承载能力以及破坏位置的方法,建立了分析其形变和渐进破坏的有限元模型,采用应力描述的二维Hashin失效准则预测材料的初始失效,并提出了一种材料受损后的刚度折减方案;由应力失效和断裂力学中的能量释放率控制材料渐进损伤的演化模式,并以损伤变量的形式表征材料的受损程度;在有限元软件ABAQUS/Standard平台上编写用户材料子程序(UMAT),运用黏性正则化方法帮助收敛,并将其预测结果与复合材料机翼长桁的压缩实验结果加以对比.结果表明,所得极限承载能力以及破坏位置的预测结果与相应的实验结果较吻合.
A method of analyzing and predicting the ultimate bearing capacity and failure location of the long-span fiber-reinforced composite girders subjected to compressive load is proposed. The finite element model for the analysis of deformation and asymptotic damage is established. The two-dimensional Hashin The failure criterion predicts the initial failure of the material and proposes a stiffness reduction scheme after the material is damaged. The gradual damage evolution of the material is controlled by the stress failure and energy release rate in fracture mechanics, and the material is characterized by damage variables The user material subroutine (UMAT) was written on the finite element software ABAQUS / Standard. The viscosity regularization method was used to help the convergence. The result of the prediction was compared with that of the composite girder The results show that the predicted ultimate bearing capacity and failure location are in good agreement with the corresponding experimental results.