Composite stiffened panels have been used in aerospace industries
for past decades. Due to light weight nature composite panels are
prone to buckling. In this study buckling load for Ortho-grid panel
and Iso-grid panel is determined. This was accomplished by
developing a composite laminate for both skin and stiffener using
MSC PATRAN/NASTRAN was used for linear buckling analysis of
composite panels. The buckling loads of two panels were determined
based on finite element analysis results, including geometric
dimension, thickness of the skin, number of laminae, ply stacking
sequence, thickness and height of stiffener. Parametric studies of
general grid stiffened panel was conducted using skin thickness,
stiffener thickness and stiffener height as design variables.
Conclusions drawn from these results are presented. All three
buckling modes appeared and maximum buckling load was observed in
skin buckling mode for Iso-grid panel.
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