Skin-stiffener structures are extensively used in the aerospace
field due to their structural efficiency in terms of
stiffness/weight and strength/weight ratios. The application of
such panels is primarily within fuselages and wing boxes, where the
weight saving potential of composite materials compared with
aluminum alloys is well known. However, design of composite panels
involves the optimization of a large number of variables such as
ply thickness and plate widths. Further complication arises when
the expert knowledge required for laminate design is considered and
when the panel is constrained by buckling under axial compression.
In this study, the behavior of Grid Stiffened Composite Cylinder is
examined under the axial compressive load. Compressive load causes
buckling and develop stresses in the structure. For the buckling
analysis two approaches are used.(1)Analytical (2)FEM. An
analytical smeared stiffener theory is used to determine buckling
load and then FEM results were compared to gain the confidence on
the developed models. The validated FEM model and analytical
smeared stiffener theory is used to conduct parametric analysis.
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