EDUCATIONAL PROGRAM FOR STRESS ANALYSIS OF AN AIRCRAFT WING BOX STRUCTURE

Gamal M.  Ashawesh; Abdoussalam M.  Elashhab; Othman A.  Alzgied

doi:10.66411/jer.v23i.304

Authors

Gamal M. Ashawesh Aeronautical Engineering Department, University of Tripoli, Libya Author
Abdoussalam M. Elashhab Aeronautical Engineering Department, University of Tripoli, Libya Author
Othman A. Alzgied Engineering Academy, Tajoura, Libya Author

DOI:

https://doi.org/10.66411/jer.v23i.304

Keywords:

Education, Program, Wing Stresses, Centre of Gravity, Shear Centre, Stiffness’s, MATLAB, Shear Flow, Wing box

Abstract

In this paper, a computer program based on the MATLAB software has been developed. The developed program is used to compute all the structural properties such as centre of gravity, shear centre, shear flows and the stresses and any point along the wing span of a given aircraft, such parameters are not available in the MATLAB software. The generalized formulation allows performing the analysis of the wing structure for both single and double wing cells with multiple stringers. The wing box consists of upper and lower skins, stringers and front and rear spars. Case studies from the open literature are considered in this paper for the validation of the developed program for both single and double wing cells.

A wing box single cell made from aluminum materials is constructed and several static tests are carried out for the validation of structure properties. The semi-span of the wing box, chord and skin thickness are 2400, 400 and 0.914 mm respectively. The wing box consists of upper and lower skins, seven ribs, four stringers and front and rear spars.

The developed program results are in the form of locations of centre of gravity, shear centre, stiffness’s, shear flows and stresses distributions at any section along the wingspan. The results of the program are in good agreement with theoretical and experimental results available in open literature.

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