In contrast with all advantages of composite materials, susceptibility of these materials to impact damage became a major concern recently. The aim of this research is to investigate the dynamic response of laminated composite cylindrical shell subjected to pure impact numerically. For this purpose, the impact of a steel ball on composite cylinder is modeled in Abaqus software as a point load and the amount of radial deflection and contact force of the contact point on cylinder surface is recorded for whole period of contact motion. To validate the obtained results they were compared with the exactly the same model in published data. According to obtained results, both of radial deflection and contact force have a parabolic variation during the impact motion. The maximum radial deflection occurs when the striker has its maximum penetration and bouncing back motion is just about to start.

Externally pressurized thin-walled GFRP composite cylindrical shell strength was studied against failure. Fiber breakage, matrix breakage, interlaminate shear deformation, delamination shear deformation and micro buckling failure were investigated employing maximum failure criteria as volumetric fiber fraction factor varied. One-ply cylindrical shell with fiber angle orientation of 0 degree was modeled in ABAQUS finite element simulation and the result was varied using analytical approaches. Moreover, the pressure fluctuations for various volumetric fiber fraction factors were quadratic according to plotted graphs obtained. Meanwhile, MATLAB software was used for theoretical analysis. The comparison of two approaches was proved to be accurate. Subsequently, failure strength of various laminated GFRP cylindrical shell with different fiber angle orientations at each ply was studied for diverse volumetric fiber fraction factors. Stacking sequence, fiber angle orientations were mainly effective on failure strength.

Due to significant amount of applications in industries, composite materials and structures are subjected to many different types of loading. One of the most common types of these loading is radial patch loading. Due to the complexity, calculation of radial shell deflection is the main character of the cylinder behavior when subjected to patch loading. The aim of this study is to investigate the mechanical behavior of composite cylindrical shell subjected to radial patch loading. The radial deflection of the laminated shell is investigated in detail where analytical and finite element methods (FEM) are used. The results through both approaches are compared to validate the accuracy of the analytical method. This is followed by a parametric study to determine the effect of some operation parameters on radial displacement. The results show close agreement between the analytical and numerical methods.