A large number of aircraft composite structures are connected by bolt fasteners,and the numerical simulation of the loading process of composite bolt joints is of great significance for the design optimization of aircraft composite structures.In order to explore an accurate simulation method for the loading process of composite bolt structures,different failure criteria and damage variables were embedded into the finite element by the ABAQUS material property definition subroutine UMAT in this paper,then the progressive damage process of composite plates was simulated effectively.The tensile tests were conducted at room temperature according to the ASTM D5961 standard.Comparing with the experimental results,it was found that the HASHIN criterion based on damage mechanism,improved HASHIN criterion and PUCK criterion could accurately predict the damage situation of composite plates.With the same failure criteria,the predicted results using sudden descent damage variables were closer to the experimental results,but at the same time,the convergence of the model would be reduced.
关键词
复合材料螺栓结构/损伤判定准则/损伤变量/有限元仿真
Key words
Composite bolt joint/Damage criteria/Damage variables/Finite element simulation
维普
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