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剪切载荷作用下复合材料加筋壁板蒙皮屈曲
引用本文:李爱环,支晗.剪切载荷作用下复合材料加筋壁板蒙皮屈曲[J].航空计算技术,2017,47(1).
作者姓名:李爱环  支晗
作者单位:中航沈飞民用飞机有限责任公司 工程研发中心,辽宁 沈阳,110000
摘    要:对复合材料加筋壁板在剪切载荷作用下的稳定性进行研究,应用PATRAN & NASTRAN软件对加筋壁板建立有限元模型进行屈曲分析,将工程分析方法四边简支条件下的蒙皮剪切屈曲载荷计算结果与加筋惯性矩刚好满足最小惯性矩要求的加筋壁板蒙皮剪切屈曲有限元仿真结果进行对比,结果吻合良好.此有限元模拟方法所得结果可以为蒙皮剪切屈曲系数的确定提供参考.改变加筋壁板加筋尺寸,研究剪切载荷作用下不同加筋尺寸对加筋壁板蒙皮屈曲的影响.

关 键 词:复合材料  加筋壁板  剪切载荷  有限元  屈曲

Skin Buckling of Composite Stiffened Panel under Shear Load
LI Ai-huan,ZHI Han.Skin Buckling of Composite Stiffened Panel under Shear Load[J].Aeronautical Computer Technique,2017,47(1).
Authors:LI Ai-huan  ZHI Han
Abstract:The stability of a composite stiffened panel under shear load is analysed.The finite element model of the composite stiffened panel is created and the buckling analysis is done with software PATRAN&NASTRAN.The engineering analysis result of the skin with all sides simply supported agrees well with the simulated result of the skin buckling under shear,in which FEM the inertia moment of stiffener equals the required minimum value.The simulated result provides reference to selection of buckling factor for the skin buckling under shear.The stiffener size is changed for the composite stiffened panel,and the effect of different stiffener size on the buckling of the skin for the composite stiffened panel is studied.
Keywords:composite  stiffened panel  shear load  finite element  buckling
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