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Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]

In airplane structural design, creating a strong yet lightweight structure is crucial. During the preliminary design phase, structural sizing optimization is necessary to achieve an efficient and lightweight structure that meets safety standards. Composite materials offer a high strength-to-weight r...

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Main Authors: Kusni, Muhammad, Syamsudin, H., Gunawan, L., Hadi, Bambang Kismono, Darmanto, Seno, Muflikhun, M. Akhsin, Widiramdhani, Martina
Format: Article
Language:English
Published: UiTM Press 2024
Subjects:
Engineering mathematics. Engineering analysis
Online Access:https://ir.uitm.edu.my/id/eprint/101340/1/101340.pdf
https://ir.uitm.edu.my/id/eprint/101340/
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spelling my.uitm.ir.1013402024-09-03T22:29:50Z https://ir.uitm.edu.my/id/eprint/101340/ Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.] jmeche Kusni, Muhammad Syamsudin, H. Gunawan, L. Hadi, Bambang Kismono Darmanto, Seno Muflikhun, M. Akhsin Widiramdhani, Martina Engineering mathematics. Engineering analysis In airplane structural design, creating a strong yet lightweight structure is crucial. During the preliminary design phase, structural sizing optimization is necessary to achieve an efficient and lightweight structure that meets safety standards. Composite materials offer a high strength-to-weight ratio, enabling a lighter structure without compromising strength. This work focuses on optimizing composite structure wings by considering laminae thicknesses as design variables and minimizing structure weight as the objective, using the gradient-based method. The optimization constraints include the Tsai-Hill criterion, buckling factor, and flutter speed to ensure the structure's safety against static load, buckling phenomena, and flutter phenomena. The optimization results indicate that the buckling factor is the most critical constraint, carrying the highest weight. The weight of the wing structure decreased by 53% and 79% after optimizing with static and flutter constraints, respectively. Despite minimal changes in weight after optimizing with the buckling constraint, the structure now meets the buckling safety criteria and is safe from buckling. UiTM Press 2024-09 Article PeerReviewed text en https://ir.uitm.edu.my/id/eprint/101340/1/101340.pdf Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]. (2024) Journal of Mechanical Engineering (JMechE) <https://ir.uitm.edu.my/view/publication/Journal_of_Mechanical_Engineering_=28JMechE=29/>, 21 (3): 16. pp. 269-295. ISSN 1823-5514 ; 2550-164X
institution Universiti Teknologi Mara
building Tun Abdul Razak Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Mara
content_source UiTM Institutional Repository
url_provider http://ir.uitm.edu.my/
language English
topic Engineering mathematics. Engineering analysis
spellingShingle Engineering mathematics. Engineering analysis
Kusni, Muhammad
Syamsudin, H.
Gunawan, L.
Hadi, Bambang Kismono
Darmanto, Seno
Muflikhun, M. Akhsin
Widiramdhani, Martina
Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]
description In airplane structural design, creating a strong yet lightweight structure is crucial. During the preliminary design phase, structural sizing optimization is necessary to achieve an efficient and lightweight structure that meets safety standards. Composite materials offer a high strength-to-weight ratio, enabling a lighter structure without compromising strength. This work focuses on optimizing composite structure wings by considering laminae thicknesses as design variables and minimizing structure weight as the objective, using the gradient-based method. The optimization constraints include the Tsai-Hill criterion, buckling factor, and flutter speed to ensure the structure's safety against static load, buckling phenomena, and flutter phenomena. The optimization results indicate that the buckling factor is the most critical constraint, carrying the highest weight. The weight of the wing structure decreased by 53% and 79% after optimizing with static and flutter constraints, respectively. Despite minimal changes in weight after optimizing with the buckling constraint, the structure now meets the buckling safety criteria and is safe from buckling.
format Article
author Kusni, Muhammad
Syamsudin, H.
Gunawan, L.
Hadi, Bambang Kismono
Darmanto, Seno
Muflikhun, M. Akhsin
Widiramdhani, Martina
author_facet Kusni, Muhammad
Syamsudin, H.
Gunawan, L.
Hadi, Bambang Kismono
Darmanto, Seno
Muflikhun, M. Akhsin
Widiramdhani, Martina
author_sort Kusni, Muhammad
title Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]
title_short Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]
title_full Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]
title_fullStr Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]
title_full_unstemmed Optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / Muhammad Kusni ... [et al.]
title_sort optimization of composite wing structure with static, buckling, and flutter constraints using the finite element method / muhammad kusni ... [et al.]
publisher UiTM Press
publishDate 2024
url https://ir.uitm.edu.my/id/eprint/101340/1/101340.pdf
https://ir.uitm.edu.my/id/eprint/101340/
_version_ 1811598206015897600
score 13.211869

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