An analysis of composite aircraft wing structures

The Finite Element Method (FEM) is used to analyze the composite wing structure of an aircraft. This analysis includes an important section of the wing Quad elements, Tri-elements, and bar elements were used to construct the finite element mesh.; This thesis includes two essentials of the inboard fuel pressure box of a wing. The first analysis summarizes the structure of the upper cover panel to represent composite wing boxes subjected to pressure loads. The numerical results from finite element analysis were compared to the experimental data obtained from the lab. The second analysis verifies the interlaminar and fiber failure region of the spar cap. This is one of the components of an inboard box that has an important physical effect on the fuel box due to the pressure loading. The finite element results were also compared with the test data for this analysis.; This thesis shows that the special mechanical properties of composite materials are competitive with common aluminum and steel. It also verifies the reduction of cost and material weight.; Over all, the research from FEM shows that the numerical results obtained were very close to the experimental lab results. However, there was a 3 percent difference in the result. This thesis concludes that the Finite Element Analysis is a reliable approach in studying composite structure.