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复合材料低速冲击损伤的特殊性及危害性使得对航空复合材料冲击损伤的评估尤为重要。该文通过建立数值计算模型并结合实验数据解决了4个方面的应用问题:1)在ABAQUS子程序VUMAT中引入损伤模式及损伤演化,结合层间连接单元对层合板低速冲击损伤进行了模拟;2)损伤容限设计方法要求对含缺陷结构的极限强度做出正确的评估,通过ABAQUS子程序USDFLD引入损伤模式及材料折减方案,得到了含圆孔的层合板极限拉压强度;3)通过ABAQUS子程序UMAT引入损伤模式及刚度折减方案,结合层间连接单元,模拟了含预制分层的层合板压缩失效问题;4)针对共用铺层结构的工程有限元计算问题,提出了力学等效模型,将该模型应用到结构级的静力实验模拟并拓展至结构冲击模拟。
The particularity and harmfulness of composite low speed impact damage make the evaluation of impact damage of aviation composite material particularly important. This paper solves the application problems of four aspects by establishing the numerical calculation model and the experimental data: 1) Introducing the damage model and damage evolution in the ABAQUS subroutine VUMAT, and simulating the low velocity impact damage of laminates by the interlayer connection element; 2) The design method of damage tolerance requires that the ultimate strength of the structure with defects should be correctly evaluated. The ABAQUS subroutine USDFLD is introduced into the damage model and material reduction scheme to obtain the ultimate tensile strength of the laminate with round holes. 3) The ABAQUS subroutine UMAT is used to introduce the damage model and the stiffness reduction scheme. Combined with the interlayer connection element, the compression failure problem of the laminate with prefabricated delamination is simulated. 4) In view of the engineering finite element calculation problem of the shared delamination structure, Equivalent model, the model is applied to structural-level static experiment simulation and extended to structural impact simulation.