Stress analysis of composite aircraft wing using coupled fluid-structural analysis

Aircraft wings are designed with very low factor of safety to keep the aircraft weight minimum. Thus, for safe design of wings, stress analysis should be carried out under accurately estimated aerodynamic loads and this can be achieved only through coupled fluid-structure analysis. Moreover, modern...

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Main Authors: Mohamed Ali, Jaffar Syed, Haron, Shahzatul Sakinah
Format: Article
Language:English
English
Published: ISSR 2021
Subjects:
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Institution: Universiti Islam Antarabangsa Malaysia
Language: English
English
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spelling my.iium.irep.935312022-01-26T03:48:52Z http://irep.iium.edu.my/93531/ Stress analysis of composite aircraft wing using coupled fluid-structural analysis Mohamed Ali, Jaffar Syed Haron, Shahzatul Sakinah TL500 Aeronautics Aircraft wings are designed with very low factor of safety to keep the aircraft weight minimum. Thus, for safe design of wings, stress analysis should be carried out under accurately estimated aerodynamic loads and this can be achieved only through coupled fluid-structure analysis. Moreover, modern aircraft wings are made of laminated composite structures and thus the purpose of this study is to employ ANSYS coupled fluid-structure analysis to find the best layup of composite wing of an aircraft that results in higher specific strength and specific stiffness. Firstly, Computational Fluid Dynamics (CFD) analysis has been carried out to find the actual aerodynamic load which is the pressure distribution around a three-dimensional wing. Then, this pressure distribution from CFD was used as a load input for detailed static structural analysis of the wing. Initially, strength and stiffness of an isotropic wing is evaluated and then the material of the wing was changed to composite laminates to achieve better structural performance with higher strength and stiffness to weight ratio. Stress analysis was carried out for different layups to predict the optimum layup that results in high strength and stiffness coupled with the least weight and it was found that the wing made of symmetric cross-ply laminate performs the best. ISSR 2021 Article PeerReviewed application/pdf en http://irep.iium.edu.my/93531/14/93531_Stress%20analysis%20of%20composite%20aircraft%20wing.pdf application/pdf en http://irep.iium.edu.my/93531/15/93531_Stress%20analysis%20of%20composite%20aircraft%20wing_Scopus.pdf Mohamed Ali, Jaffar Syed and Haron, Shahzatul Sakinah (2021) Stress analysis of composite aircraft wing using coupled fluid-structural analysis. CFD Letters, 13 (11). pp. 78-86. ISSN 2180-1363 10.37934/cfdl.13.11.7886
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
language English
English
topic TL500 Aeronautics
spellingShingle TL500 Aeronautics
Mohamed Ali, Jaffar Syed
Haron, Shahzatul Sakinah
Stress analysis of composite aircraft wing using coupled fluid-structural analysis
description Aircraft wings are designed with very low factor of safety to keep the aircraft weight minimum. Thus, for safe design of wings, stress analysis should be carried out under accurately estimated aerodynamic loads and this can be achieved only through coupled fluid-structure analysis. Moreover, modern aircraft wings are made of laminated composite structures and thus the purpose of this study is to employ ANSYS coupled fluid-structure analysis to find the best layup of composite wing of an aircraft that results in higher specific strength and specific stiffness. Firstly, Computational Fluid Dynamics (CFD) analysis has been carried out to find the actual aerodynamic load which is the pressure distribution around a three-dimensional wing. Then, this pressure distribution from CFD was used as a load input for detailed static structural analysis of the wing. Initially, strength and stiffness of an isotropic wing is evaluated and then the material of the wing was changed to composite laminates to achieve better structural performance with higher strength and stiffness to weight ratio. Stress analysis was carried out for different layups to predict the optimum layup that results in high strength and stiffness coupled with the least weight and it was found that the wing made of symmetric cross-ply laminate performs the best.
format Article
author Mohamed Ali, Jaffar Syed
Haron, Shahzatul Sakinah
author_facet Mohamed Ali, Jaffar Syed
Haron, Shahzatul Sakinah
author_sort Mohamed Ali, Jaffar Syed
title Stress analysis of composite aircraft wing using coupled fluid-structural analysis
title_short Stress analysis of composite aircraft wing using coupled fluid-structural analysis
title_full Stress analysis of composite aircraft wing using coupled fluid-structural analysis
title_fullStr Stress analysis of composite aircraft wing using coupled fluid-structural analysis
title_full_unstemmed Stress analysis of composite aircraft wing using coupled fluid-structural analysis
title_sort stress analysis of composite aircraft wing using coupled fluid-structural analysis
publisher ISSR
publishDate 2021
url http://irep.iium.edu.my/93531/14/93531_Stress%20analysis%20of%20composite%20aircraft%20wing.pdf
http://irep.iium.edu.my/93531/15/93531_Stress%20analysis%20of%20composite%20aircraft%20wing_Scopus.pdf
http://irep.iium.edu.my/93531/
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