Stiffened Panel Virtual Test

In the structural design of aircraft, low weight is as important as reliability and strength. In airplanes, designs must have an optimum weight and strength ratio in order to prevent high fuel consumption and increase the useful load carrying capacity. In this study; Reinforced panel designs with different number of rivets subjected to compression load under the same conditions are modeled by the finite element method. Aim; It is to find the most effective number of rivets in the panels by optimizing the ratio of the distance between the rivets to the rivet diameter. For this purpose, 8 different panels with rivet reinforcement were modeled with the ANSYS package program. Z type reinforcement was used in each panel. Nonlinear buckling analyzes were performed under the same boundary conditions and compression load. The initial buckling and buckling loads were obtained by referring to the graph of the “displacement-force” curve obtained as a result of the analyses. In the finite element model; The changes in the initial buckling loads and collapse loads were investigated by increasing the distance between the rivets and the rivet diameter ratio from 4 to 6.1. According to the results obtained, it has been observed that the ratio of distance between rivets and rivet diameter, which minimizes stress concentrations, is 4.5 for the optimization made in the rivet reinforced model. After this ratio, although there are partial decreases in the buckling load strength, serious decreases occur in the collapse load strength. Therefore, it was concluded that the ratio of 4.5 is the minimum ratio that maintains the collapse load strength at an optimum level.