作者: Y.B. SudhirSastry , Pattabhi R. Budarapu , N. Madhavi , Y. Krishna
DOI: 10.1016/J.COMMATSCI.2014.06.007
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摘要: Abstract We present the pre and post buckling analysis of stiffened composite panels based on finite element models. Individual studies are conducted panel madeup woven fabric CFC/epoxy, E-glass/epoxy Kevlar/epoxy composites. Straight, T shaped I stiffeners considered to stiffen panel. The is fabricated with 8 layers 16 layers, equal thickness arranged in different orientations. subjected a uniform axial compression load 10 kN. distribution stresses loads stiffener combinations estimated for three layup sequences. variation from numerical model compared experiment. results excellent agreement.