Buckling behavior of laminated composite stiffened cylindrical shell panels having cutout for different parametric variations

Abstract

Buckling of composite stiffened cylindrical shell panels having cutout is analyzed using the finite element approach. Shell panel and stiffeners are modeled using first-order shear deformation theory and considering displacement compatibility at the stiffener-panel interface. Convergence and validation studies are conducted to establish the accuracy of the present approach. An attempt is made to maximize the uniaxial and biaxial buckling loads by varying the lamination, boundary conditions, load position, depth of stiffeners, and their arrangements. Parametric studies show that buckling load and mode shapes depend on the size of cutout, ratio of shell width to thickness, degree of orthotropy, and fiber orientation angle. The parametric variations considered here may help the practicing engineers to have an elaborate design aid for improving the buckling strength of such shell panels.

Analytical investigation on the buckling of cylindrical shells under combined non-uniform axial compression and external pressure

“…In their paper, both external pressure and axial compression were taken into consideration, and existing formula to predict buckling loads was modified. Based on FE analysis, Sahoo 14 discussed the buckling of composite stiffened cylinders with cutout under various loading conditions.…”