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《Materials for Mechanical Engineering》 2013-03
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FEM Analysis on Compress Buckling Stability of Stiffened Aluminum Alloy Panels

YE Guang-ning1,SHAO Qing2,HE Yu-ting2,FENG Yu2(1.Navy Equipment Department,Xi′an 710038,China; 2.Aeronautics and Astronautics Engineering College,Air Force Engineering University,Xi′an 710038,China)  
Finite element software MSC.PATRAN/NASTRAN was applied to calculate compress buckling critical loads and analyse buckling modes of six types of stiffened aluminum alloy panels with T/Z-section stringers,and the results calculated by FEM were compared with semi-empirical calculation results.The results show that,with same cross section area,reducing stringer pitch or increasing stringer numbers could improve buckling critical loads.Buckling critical loads of T-stringer panels were higher than that of Z-stringer panels with the same stringer pitch and numbers.The first rank buckling mode of T-stringer panels presented local buckling of skin or general buckling of panel,while that of Z-stringer panels all presented local buckling of skin.The FEM simulation results were accordant with semi-empirical calculation results.Comparing with T-stringer panels,the errors between the two calculation results of Z-stringer panels were smaller.
【CateGory Index】: TB332
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