应用桥联理论与有限元模型的航空复合材料结构失效分析

桥联理论是一个近年来发展迅速的细观力学理论，它仅需纤维和基体材料的力学性能即可预报复合材料的响应。考虑基体应力集中系数与界面脱粘的影响后，大幅提高了复合材料破坏与强度的预报精确度。本文通过商业有限元（FE）软件ABAQUS的二次开发功能，将桥联模型的最新发展编写入UGENS子程序，并对复合材料单层板、层合板以及航空航天工业常见的T型接头复杂结构进行了有限元强度分析，并与实验结果进行对比，结果吻合良好。

Failure analysis of aeronautic composite structures incorporated with bridging model and FE model

The bridging model is a micromechanical theory for composites with rapid development in resent years. One of its significant features is in that only properties of the fiber and matrix of the composite constituent are required to predict the response of the composite materail. Taking the stress concentration factors of the matrix and the interface debonding effect into account greatly enhance the prediction accuracy. In this paper, all of the latest developments of the bridging model have been programmed into a user subroutine, UGENS, of commercial Finite Element (FE) software ABAQUS's secondary development function. The strength behaviors of the composite lamina, laminate, and a complicated T-joint structure used widely in the aerospace field are then analyzed with the software. The calculated results agree well with the available experimental data.