Stress analysis of laminated graphite fiber reinforced polymer Panel Stiffened joint with 450 fiber orientation using ANSYS

Abstract

Large panels made of composite materials are utilised often in the aerospace sector. In most cases, this type of panel will fracture when subjected to a wide variety of stresses and boundary conditions. The panel receives additional rigidity through the addition of a flange, which is also supported by a web. In this study, a three-dimensional finite element stress analysis is performed on a firm panel that consists of a web, a flange, and a panel with an interface between the flange and the panel. The analysis is performed in preparation for an arrangement of composite panels of this sort. The influence that anisotropy, layer stacking sequence, and ply orientation have on the stress components is taken into consideration. For the purpose of this investigation, a graphite-fiber reinforced polymeric (GFRP) composite is used. Laminate arrangements of [45 0 /–45 0 /45 0 /–45 0 ] 2 and [45 0 /–45 0 2 /45 0 ] 2 angle-plied prepregs have been taken. This work makes use of the coupled stress failure criterion in order to forecast the site where damage initiation would take place. The critical point is observed to be around the layer’s front-left border, with a maximum stress concentration of about 125 MPa. Stress values fall as they move from left to right. Negative stress component values have also been observed in a few cases.