Investigation of buckling and modal analysis of stiffened panels

The contributions of the aviation industry, which leads the technology developments, to the material science and manufacturing methods are increasing day by day. It continues to use all the possibilities of engineering by going beyond its usual methods of by bringing innovation to the existing method. Stiffened integrated panels, which are frequently used in aircraft structures, were generally designed not to be monolithic with different connection methods. The innovation of monolithic manufacturing of stiffened integrated panels has played an active role in reducing assembly times in aircraft. In addition, we can say that it significantly reduces the use of fasteners and adhesive materials to be used for assembly. This study employs the finite element method (FEM) to analyze the behavior of a stiffened integrated panel. The panel is composed of a thin plate with stiffeners attached to its surface. The FEM model is used to simulate the panel under various loading conditions and the results are analyzed to determine the panel's strength, stiffness, and overall behavior. The study emphasized that it is critical to accurately simulate the test environment in the FEM environment, as the reinforced integrated panel plays a crucial role in increasing the strength and rigidity. The results of this study can be used to design and analyze similar structures in the future.