• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Thin-Walled Structures >The computational post buckling analysis of fuselage stiffened panels loaded in compression
【24h】

The computational post buckling analysis of fuselage stiffened panels loaded in compression

机译：压缩加载机身加强面板的计算后屈曲分析

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

Fuselage panels are commonly fabricated as skin-stringer constructions, which are permitted to locally buckle under normal flight loads. The current analysis methodologies used to determine the post buckling response behaviour of stiffened panels relies on applying simplifying assumptions with semi-empirical/empirical data. Using the finite element method and employing non-linear material and geometric analysis procedures, it is possible to model the post buckling behaviour of stiffened panels without having to place the same emphases on simplifying assumptions or empirical data. Investigation of element, mesh, idealisation, imperfection and solution procedure selection has been undertaken, with results validated against mechanical tests. The research undertaken has demonstrated that using a commercial implicit code, the finite element method can be used successfully to model the post buckling behaviour of flat riveted panels. The work has generated a series of guidelines for the nonlinear computational analysis of flat riveted panels subjected to uniform axial compression.
机译：机身面板通常由皮肤纵梁结构制成，允许在正常的飞行负荷下局部扣。用于确定加强面板的后屈曲响应行为的当前分析方法依赖于使用半经验/经验数据来应用简化假设。使用有限元方法和采用非线性材料和几何分析程序，可以模拟加强面板的后屈曲行为，而无需在简化假设或经验数据上放置相同的重点。对元素，网格，理想，缺陷和解决方案选择进行了调查，结果验证了机械测试。进行的研究已经证明，使用商业隐式码，可以成功使用有限元方法来模拟扁平铆接面板的后屈曲行为。该工作为扁平铆接面板的非线性计算分析产生了一系列指南，该面板经受均匀轴向压缩。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号