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模拟X型号飞机复合材料机翼有限元分析
  • 期刊名称:沈阳航空航天大学学报,2011;28:48-51
  • 时间:0
  • 分类:O343.8[理学—固体力学;理学—力学] V214.8[航空宇航科学与技术—航空宇航推进理论与工程;航空宇航科学技术]
  • 作者机构:[1]沈阳航宽工业学院航空宇航工程学院,辽宁沈阳110136
  • 相关基金:国家自然科学基金项目(10802052)
  • 相关项目:复合材料层合板精化高阶理论和分层分析
中文摘要:

该文基于锯齿理论构造了两节点梁单元,并用此单元分析了软核夹层梁屈曲问题。该文使用的锯齿理论能够预先满足层间应力连续条件,并且未知变量的个数独立于层合梁的层数。为了说明锯齿理论的准确性,Reddy理论和一阶理论也被选择作为比较。数值结果表明:基于锯齿理论构造的梁单元能够准确的预测软核夹层梁的临界载荷,然而Reddy理论和一阶理论明显高估了此结构临界载荷。

英文摘要:

Based on the zig-zag theory,a two-node beam element is constructed.Moreover,this element is used to analyze the buckling problems of soft-core sandwich beams.The zig-zag theory used herein can become a priori condition for satisfying interlaminar continuity of transverse shear stresses,and the total number of unknowns is independent of the layer number of laminated beams.At the same time,Reddy's theory as well as first-order theory is chosen for comparison.Numerical results show that beam element based on zig-zag theory is able to accurately predict critical loads of soft-core sandwich beams.However,Reddy's theory and first-order theory obviously overestimate the buckling response of the special structures.

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