论文部分内容阅读
针对含离散源损伤复合材料机翼壁板机械连接修理结构,开展了机械连接修理结构渐进式破坏有限元分析技术的研究和验证。建立了利用梁元耦合解析刚性面模拟螺钉,采用适用于平面应力状态的LaRC05强度准则和B-K准则作为复合材料层板和胶接界面失效判据的机械连接修理结构有限元分析模型。在此基础上,通过编写用户自定义材料子程序(UMAT),实现了材料失效准则与刚度退化方案在商用软件Abaqus中的应用和机械连接修理结构承载能力的求解。计算结果表明,对于大规模螺钉连接的复杂修理结构,所采用的有限元建模和分析方法有效可行。与试验结果相比,结构承载能力数值分析与试验值吻合良好,误差在5%以内,预测的失效模式也与试验结果一致。
Aiming at the mechanical connection repair structure of wing panels with composite materials with discrete source damage, the finite element analysis of the progressive failure of the mechanical connection repair structure is carried out. A finite element analysis model of mechanical connection repair was established by using beam-element coupled analytical rigid surface model screw and LaRC05 strength criterion and B-K criterion suitable for plane stress state as failure criteria of composite laminates and cemented interface. On this basis, the application of material failure criterion and stiffness degeneration scheme in commercial software Abaqus and the solution of bearing capacity of mechanical connection repair structure are realized by compiling user-defined material subroutine (UMAT). The calculation results show that the method of finite element modeling and analysis is effective and feasible for the complicated repair of large-scale screw connections. Compared with the test results, the numerical analysis of structural load-bearing capacity is in good agreement with the experimental values, with the error within 5%. The predicted failure modes are also consistent with the test results.