Title: Design and Stress Analysis of Wing Structure for a Military Transport Aircraft – Cessna Citation V (560).
Authors: Ms.B.Alekhya, Midatanapally Vinod Kumar & Dr.M.Satyanarayana Gupta
Organisation: MLR Institute of Technology and Management.
ABSTRACT This project deals with the structural analysis of wing. The aim of this project work is to design and analyze the wing of a military 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 3Dimensional 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. 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 modeling, 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 and displacement of a wing structure is determined.
Keywords: Composite wing, CATIAV5, Finite Element Modeling, MSC PATRAN & NASTRAN, linear static analysis, Compressive stress, Torsion, shear force bending moment.
To download the above Complete paper in PDF format Click on below Link: