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FROM:
R.S. Priyadarsini and V. Chitra (Department of Civil Engineering, College of Engineering, Trivandrum, Kerala, India),
“Dynamic Buckling of Advanced Fibre Composite Cylindrical Shells under Axial Impact”, International Journal of Engineering and Management Research, Vol. 6, No. 1, pp 136-157, January-February 2016
ABSTRACT: Advanced lightweight laminated composite shells are increasingly being introduced in designs of modern aerospace structures, for enhancing their structural efficiency and performance. They are susceptible to buckling when subjected to significant static and dynamic or time dependent loadings. Their strength as governed by buckling is affected by initial geometric imperfections, boundary conditions, lamina stacking sequence and load eccentricity. While numerous studies are available on the buckling and post buckling behaviour of isotropic shells and the effects of geometric imperfections, relatively few investigations have been undertaken on the laminated composite shells for dynamic loading conditions. The need to design shell structures that have to withstand time-dependent dynamic loads, sometimes quite severe, and thus may be susceptible to dynamic buckling is relatively new in aerospace structures. The term dynamic buckling refers to two different phenomena. One is associated with the response of the structure to the action of cyclic loads i.e. vibration buckling, and the second one relates to the behaviour of structures subjected to pulse loads. The presence of imperfections may also adversely affect the buckling behaviour of the shells. This paper deals with a numerical study on the effect of different shell parameters and imperfections on the buckling behaviour of circular cylindrical composite shells under axial impact. Composite cylindrical shells with three different layups [0°/0°/60°/- 60°] s , [0°/45°/-45°/0°] s and [75°/-75°/75°/-75°] s , each having different length to radius ratios (L/R) and radius to thickness ratios (R/t) have been considered in this study.
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