Design and analysis of hybrid aircraft wing root rib structure with different geometries

Aircraft wing ribs are a structural element that provides space for systems such as fuel tanks and landing gear to be placed in the wing, gives the aerodynamic shape of aircraft wings and increases the load-bearing capacity of the wing by supporting the structure by optimizing the distribution of loads on the wing. Thanks to the advances in materials science, materials such as composite materials have emerged that are more durable and long-lasting than traditional materials. These developments have also led to revolutionary results in the field of aviation, and the use of composite materials in aviation has gradually increased due to their excellent properties compared to traditional materials. The main topic of this thesis is the application of composite materials, which are widely used in almost every field today, to aircraft wing ribs. In this thesis, the design and analysis of composite aircraft wing root rib structures of different geometries are discussed. The design and analysis operations were carried out using computer aided design (CAD) software and finite element analysis (FEA). The composite materials used in this thesis are Carbon Epoxy, Kevlar I Epoxy, Kevlar II Epoxy and hybrid materials obtained from the combination of these three composite materials. However, the fiber angles of the composite materials used 0°,15°,30°,45°,60°,75° and is 90°.