复合材料加筋结构后屈曲的自开发程序

发布时间：2018-03-23 01:30

本文选题：材料失效　切入点：结构破坏　出处：《复合材料学报》2017年07期 　论文类型：期刊论文

【摘要】：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。
[Abstract]:Aiming at the post-buckling problem of composite laminated stiffened structures, a self-made Fortran program is developed and embedded in Patran to deal with the post-buckling problem. The linear buckling mode is calculated by the program, which is used as the initial deflection of nonlinear post-buckling calculation. The incremental iterative technique, arc length control and energy convergence criterion are used to solve nonlinear equations. Finally, the composite Tsai-Hill failure criterion is introduced. The damage of the element is judged and the stiffness is reduced. The compression test of composite stiffened plate is used to verify the system. The calculation and analysis of post-buckling by this system show that the numerical results are in good agreement with the experimental data.
【作者单位】：西北工业大学航空学院;沈阳飞机设计研究所;
【分类号】：TB33

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