Optimization of Light Weight Aircraft Wing Structure

المؤلفون

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

الكلمات المفتاحية:

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الملخص

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.

التنزيلات

Key Dates

منشور

2008-03-01

إصدار

مجلد 12 عدد 1 (2008): Journal of Engineering and Development

القسم

Articles

الرخصة

Creative Commons License

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Creative Commons-Attribution (BY)

كيفية الاقتباس

Optimization of Light Weight Aircraft Wing Structure. (2008). مجلة الهندسة والتنمية المستدامة, 12(1), 1-22. https://jeasd.uomustansiriyah.edu.iq/index.php/jeasd/article/view/1632