Within the scope of this study, a CATIA project was used to create a thorough design of a trainer aircraft wing structure. After that, a stress analysis of the wing structure is carried out in order to calculate the stresses that are being placed on the wing structure. In order to calculate the structure's safety factor, the finite element method along with ANSYS's assistance is used to make an estimate of the stresses. In a structure such as an aircraft, a fatigue fracture could develop at the spot where the tensile stress is the highest. Life prediction necessitates the use of a model for the accumulation of fatigue damage, constant amplitude S-N (stress life) data for a variety of stress ratios, and local stress history at the stress concentration. It is planned to analyse the reaction of the structure of the wing. The complete investigation of the trainer aircraft wing structure, including the skin, spars, and ribs, is the focus of this particular piece of research. The structure of the wing is made up of 15 ribs and two spars that are covered with skin. A "I" segment is located on the front spar, while a "C" section is located on the rear spar. In order to calculate the stresses that will be placed on the spars and ribs as a result of the imposed pressure load, a stress and fatigue study of the whole wing section must first be performed. Aircraft wing, CATIA, Ansys, static analysis, and fatigue life prediction are some of the keywords that may be found here.

Within the scope of this study, a CATIA project was used to create a thorough design of a trainer aircraft wing structure.