Optimization of Light Weight Aircraft Wing Structure

Authors

  • Muhsin J. Jweeg Mechanical Eng. Dept., College of Eng., Al-Nahrain University, Baghdad, Iraq Author
  • Shawkat J. Al-Tornachi Mechanical Engineering Dept., University of Technology , Baghdad, Iraq Author
  • Salah H. Abid-Aun Mechanical Eng. Dept., College of Eng., Institute of Technology, Baghdad, Iraq Author

Keywords:

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Abstract

In this paper, the static analysis for finding the optimum design of wing structure has been performed. The two types of wings for unmanned airplanes were chosen; the first wing was the taper designed at (M=0.71) and the other wing was rectangular designed at (M=0.21). The research covers both aerodynamic and structural design. The aerodynamic study was achieved by using the vortex lattice method and the structural analysis was achieved by using the Ansys 5.4 package where isotropic and composite materials were
used. From the results the mass saving of (32%) when composite material is used instead of isotropic material for the taper wing and (23%) for the rectangle wing. The optimum design for each wing was obtained according to the mass, stress, and displacement.

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Key Dates

Published

2008-03-01

Issue

Vol. 12 No. 1 (2008): Journal of Engineering and Development

Section

Articles

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This work is licensed under a Creative Commons Attribution 4.0 International License.

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How to Cite

Optimization of Light Weight Aircraft Wing Structure. (2008). Journal of Engineering and Sustainable Development, 12(1), 1-22. https://jeasd.uomustansiriyah.edu.iq/index.php/jeasd/article/view/1632