The purpose of this paper is to describe the finite element modelling studies that were performed to develop a composite advanced stiffened shell structure which would be used in Launch vehicle application. Interstage structure is a cylindrical barrel that is axially compressed but also withstands crushing and internal pressure causing compressive and tension hoop panel loads. It is essential that launch vehicle structures should be designed to minimum weight and at the same time it has to withstand the loads and the various forces imposed. So these structures should have high bending stiffness and resistance to buckling under compression. CFRP Composite shell structures are finding many applications in the field of aerospace because of its high strength and stiffness to weight ratio and damage tolerance. Impact damage has been an epidemic problem for composite structures. There is a necessity to improve the structural efficiency of these structures to withstand various loads, especially axial compression and impact loading. In the present paper, the structural design and analysis were performed using by SolidWorks® software and LS-DYNA® finite element analysis software for the advanced CFRP composite cylindrical shells viz., blade stiffened, bonded hat and grid stiffened under impact loading conditions. The material model and material properties of the entire FEA is based upon the experimental test results.

Keywords: CFRP, Impact, LS-DYNA®, Blade stiffened, Bonded hat, Grid stiffened.