Paper Title:

Structural Analysis of Light Aircraft Wing Components

Periodical Applied Mechanics and Materials (Volume 225)
Main Theme AEROTECH IV
Chapter Chapter 2: Aerospace Structures and Material
Edited by R. Varatharajoo, E. J. Abdullah, D. L. Majid, F. I. Romli, A. S. Mohd Rafie and K. A. Ahmad
Pages 201-206
DOI 10.4028/www.scientific.net/AMM.225.201
Citation Abdelmunem Bushra et al., 2012, Applied Mechanics and Materials, 225, 201
Online since November 2012
Authors Abdelmunem Bushra, Mohammed Mahdi, Mohammed A. Elhadi
Keywords Finite Element Method (FEM), NASTRAN, PATRAN, Structure Analysis, Strut-Braced Wing
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This paper aims to demonstrate the structure analysis of strut-braced wing of a typical manufactured Light-Aircraft by using FEM software (MSC PATRAN/NASTRAN) and determine the safety margin in all of its components, which are useful to determine the structure strength requirements. The geometrical model of the wing was created in CATIA and then exported to PATRAN, which is the modeler to build the finite element model. PATRAN model geometry was modified and prepared to create the mesh. The structural components have various functions and shapes, thus different element mesh was created. After creating the finite element model for all parts, the elements and material properties were assigned and the model was fixed at the spar root edge and strut-braced end, and loaded by distributing the inertia load and aerodynamic load, calculated using (CFD), acting on the rib edge. Then the model was submitted to NASTRAN for linear static analysis. The obtained Stress Results and Safety Margins of each part were calculated and found to be acceptable.