摘要
应用非线性有限元分析技术,采用MSC.Patran为前后置处理器进行建模,以具有较强非线性功能的Marc软件为求解器,细致研究了某民机中央翼加筋板结构在受力状态下的非线性变形、后屈曲破坏过程、最终失稳破坏形式及载荷,与试验结果进行了比较,破坏过程及破坏形式与试验相吻合,计算的破坏载荷与试验的破坏载荷误差在5%以内,显示文中方法可以满足工程设计和分析要求。
The buckling failures of stiffened panels of the civil central wings subjected to axial- loads were investigated by nonlinear FEM. The software of MSC. Patran and MSC. Marc were used to act as prepro- cessor, post- processor and solver, the failure deformation and loads were presented. Results reveal that compared with experimental data, the failure loads are in agreement with experimental loads. The average relative errors of predicted failure loads are within 5% , which shows that the method is helpful to engineer designers.
出处
《航空计算技术》
2012年第3期42-45,共4页
Aeronautical Computing Technique
基金
航空科学基金项目资助(20090923006)
关键词
民机
中央翼
承载能力
非线性有限元分析
civil aircraft
central wing
capacity load
nonlinear finite element method
