Structural design of aircraft wing with using integratedstiffened panel

Materials and manufacturing methods used in aerospace industry have been improved in recent years because of huge technological developments. Wood was the first material utilized in aircraft manufacturing, but currently integrated structures, additive manufacturing and composite materials are used. Through these new generation materials and manufacturing methods lighter and stronger aircraft structures can be designed and manufactured. In this work, by using the panel method, one of the new generation manufacturing methods, an aircraft wing panel was designed. The main purpose of this work is to investigate effects of different stiffener geometry and panel structures in terms of buckling performance. Improved buckling performance benefits the aerospace industry by decreasing the number of parts. This method also helps reduce the manufacturing time, number of fasteners and fastener holes, potential crack start points and access requirements for the assembly process. Four different geometries of integrally-stiffened panel and one build-up panel are designed and compared in this work. The weight, assembly and costeffective designs can be carried out on panels subject to compressive loading, especially upper wing panels, by using results of this work.