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Article

Graphite-Epoxy Composite Design for Aircraft Wing Skin Using Computational Techniques - Part II

1Department of Mechanical Engineering, Nigerian Defence Academy, Kaduna, Nigeria


American Journal of Mechanical Engineering. 2017, Vol. 5 No. 5, 175-198
DOI: 10.12691/ajme-5-5-1
Copyright © 2017 Science and Education Publishing

Cite this paper:
Akindapo Jacob Olaitan, Johnson-Anamemena Nnaemeka, Garba Danladi King. Graphite-Epoxy Composite Design for Aircraft Wing Skin Using Computational Techniques - Part II. American Journal of Mechanical Engineering. 2017; 5(5):175-198. doi: 10.12691/ajme-5-5-1.

Correspondence to: Akindapo  Jacob Olaitan, Department of Mechanical Engineering, Nigerian Defence Academy, Kaduna, Nigeria. Email: jacobakindapo@gmail.com

Abstract

This present work is on graphite-epoxy design for light weight high performance structure of an aircraft wing skin using computational technique. MATLAB MuPAD software was used to derive an analytical model for aircraft wing loads using symbolic computation to estimate the shear force acting on the wings while Autodesk Simulation Composite Design and ANSYS 14 Mechanical APDL (ANSYS Parametric Design Language) software were used to design and analyze the idealized composite structures of the wing skin. An idealized structure such as a flat plate which is a good approximation for the purposes of preliminary design and analysis was first developed using Autodesk Simulation Composite Design. After which, finite element analysis was also employed using ANSYS 14 Mechanical APDL to provide progressive failure analyses of the graphite-epoxy composite structures in order to determine the in-plane shear stress, displacement and other desired mechanical properties that would aid in material selection during fabrication and manufacturing. This investigation reveals that to withstand shear force of 3,000N for wing skin laminates designs, High Modulus (HM) and Ultra Modulus (UM) with [(+/-45)s] stacking sequence offers the best maximum shear stress output of 0.1991010 N/m2 prior to delamination. For failure prediction, Low Modulus (LM) and Ultra Modulus (UM) with [(+/-45)s] design has the best property prior to failure at 0.4991010 N/m2. HM and UM with [(+/-45/0/90)s] stacking sequence demonstrates the least compressive deformation of 0.004195m.

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