This paper aims at performing linear static analysis of laminated composite interface ring of rocket launcher and to investigate the effect of ply orientation of laminates on deformation and stress pattern. The interface ring is a part of conical shell, having a top radius of 367mm and bottom radius of 472mm. The shell is made of laminated carbon fibre plastic composites with distribution of total of 20 layers forming a total thickness of 2mm. The load of 200kN from the components above the ring acts as distributed compressive load on the top of the ring, the bottom of which is fixed. The analysis carried out on structure lead to best suited laminate and optimum ply orientation. The minimum deformation for laminated conical shells having angle plies is obtained with a ply orientation of 10 degree.
展开▼
