• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>The Aeronautical Journal >Optimum design for buckling of arbitrary shaped ribs under uncertain loadings
【24h】

Optimum design for buckling of arbitrary shaped ribs under uncertain loadings

机译：不确定载荷下任意形状肋条屈曲的优化设计

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

Typically, aircraft wing structural panels are designed against buckling for a very large number of possible loadings that may occur during the operation of the aircraft. If the optimisation procedure accounts only for a limited number of design loads, the structure may be vulnerable to a specific type of loading that may cause the structure to fail. A novel approach for the optimisation of ribs or plates of arbitrary shapes under uncertain loads is proposed. The geometry of the rib is defined by a single closed spline or several connected splines. The loading distribution is not considered to be uniform but it is allowed to vary within an admissible set, conferring uncertainty to the applied loads. The admissible load space comprises distributed normal and shear loadings that can be represented through a collection of piecewise linear functions defined along the plate boundary. A special procedure is applied to handle the constraint that the loading must be self equilibrating. A minimax strategy is used to deal with the loading variability such that the resulting optimal design is able to withstand an entire class of linear piecewise loadings along the rib boundary. The refinement of the loading representation may be completely independent of the refinement of finite element mesh. The validity of the proposed approach is assessed by applying it to an aeronautical wing rib.
机译：通常，飞机机翼结构板被设计成防止屈曲，以承受在飞机运行期间可能发生的大量可能的载荷。如果优化过程仅考虑有限数量的设计载荷，则结构可能易受特定类型的载荷的影响，这可能会导致结构失效。提出了一种在不确定载荷下优化任意形状的肋或板的新颖方法。肋的几何形状由单个闭合花键或多个连接的花键定义。载荷分布不被认为是均匀的，但允许在允许的范围内变化，从而给所施加的载荷带来不确定性。允许的载荷空间包括分布的法向载荷和剪切载荷，这些载荷可以通过沿板边界定义的分段线性函数的集合来表示。应用了特殊的程序来处理这种约束，即负载必须是自平衡的。使用最小最大策略来处理载荷的可变性，以使最终的最佳设计能够承受沿肋骨边界的整个线性分段载荷类别。载荷表示的细化可以完全独立于有限元网格的细化。通过将其应用于航空翼肋来评估所提出方法的有效性。

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