DESIGN AND STRUCTURAL ANALYSIS OF TRANSPORT AIRCRAFT WING

This project deals with the structural analysis of transport aircraft wing. The aim of this project work is to design and analyse the wing of a transport aircraft, and to obtain the Stress and displacement due to the applied loads. For this we did a comparative study on particular transport aircraft. The optimum design parameters for a transport aircraft are suitably selected based on the classical method of calculations and then a 3-Dimensional model of the wing structure will be designed using the CATIA-V5 software, which is developed by Dassault systems and is very famous for its 3D modeling capabilities. The Major loads acting on the aircrafts wing are determined and the bending moments, shear force etc., are also determined. The wing structure was also explained and functions of each component and their arrangement are also studied. The methodology of finite element method and the detailed description about various FEM tools have been studied and implemented in this work. The linear static analysis carried out using MSC Nastran and Patran, patran is used for carrying out operations like importing the geometry, Finite element modelling , defining material properties , Loads and cross sectional properties of the structure , whereas Nastran is used for as a solver. When carrying out a linear static analysis, in the finite element method the stress of a wing structure is determined.