论文部分内容阅读
针对复合材料层合加筋结构的后屈曲问题,开发出自编Fortran程序,并嵌入Patran进行前后处理。采用该程序计算出线性屈曲模态,将其作为后屈曲非线性计算的初始挠度;采用增量迭代技术、弧长控制及能量收敛准则求解非线性方程;最后引入复合材料Tsai-Hill失效准则,对单元的损伤进行判断及刚度折减。采用复合材料加筋板的压缩试验对该系统进行初步验证。针对不同加载方式、选材及结构型式的机翼盒段,利用该系统进行后屈曲计算和分析,数值结果与试验数据吻合较好。
Aiming at the post-buckling problem of the composite laminated stiffened structure, a Fortran program was developed and embedded in Patran for pre-postprocessing. The program was used to calculate the linear buckling mode, which was used as the initial deflection of post-buckling nonlinear calculation. The nonlinear equations were solved by incremental iteration technique, arc length control and energy convergence criterion. Finally, Tsai-Hill failure criterion was introduced, Determine the unit damage and stiffness reduction. The system was preliminarily verified by compression test of composite stiffened plates. According to the wing boxes with different loading methods, material selection and structural types, post-buckling calculation and analysis are carried out by the system. The numerical results are in good agreement with the experimental data.