Cover Image

The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method

Composite material has been widely used in aircrafts due to its high strength to weight ratio that leads to weight saving of the aircrafts. Equally important, aircraft material should be tough i.e. it should have the ability to absorb high energy and thus resist fracture. The aircraft’s wing design...

Full description

Saved in:
Bibliographic Details
Main Authors: Omar, Nurihan, Aminanda, Yulfian, Mohamed Ali, Jaafar Syed, A. Rasid, Zainudin, Yahaya, Hafizal
Format: Article
Language:English
English
Published: Blue Eyes Intelligence Engineering and Sciences Publication 2019
Subjects:
TK Electrical engineering. Electronics Nuclear engineering
Online Access:http://irep.iium.edu.my/79862/1/79862_The%20Impact%20Behaviour%20of%20Carbon.pdf
http://irep.iium.edu.my/79862/2/79862_The%20Impact%20Behaviour%20of%20Carbon_SCOPUS.pdf
http://irep.iium.edu.my/79862/
https://www.ijrte.org/wp-content/uploads/papers/v8i2/B3013078219.pdf
Tags: Add Tag
No Tags, Be the first to tag this record!
id my.iium.irep.79862
record_format dspace
spelling my.iium.irep.798622020-03-26T07:47:31Z http://irep.iium.edu.my/79862/ The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method Omar, Nurihan Aminanda, Yulfian Mohamed Ali, Jaafar Syed A. Rasid, Zainudin Yahaya, Hafizal TK Electrical engineering. Electronics Nuclear engineering Composite material has been widely used in aircrafts due to its high strength to weight ratio that leads to weight saving of the aircrafts. Equally important, aircraft material should be tough i.e. it should have the ability to absorb high energy and thus resist fracture. The aircraft’s wing design requires the material to have high toughness as parts of the wing especially its leading edge is subjected to impact loadings. Using finite element software of LS-DYNA, this research focuses on studying the impact behaviour of composite panels that represent the leading edges of wings when the panels are subjected to rigid sphere projectile. Three shapes of panels are used: flat, semi-circular and semi ellipse while panels can be of 2, 4 and 8 layers to vary its thickness. The panels are made of laminated composites with woven carbon fibres and the angle of orientations are [0/90] n, [0/45]n and [45/-45]n where n will give the number of layer for the composite. The Mat-58 material type suitable for woven type fibre is used where failure criteria of Hashin is applied. It was found that the simulation results are in a very close agreement with the finding from experiments conducted earlier. Furthermore, the optimum stacking sequence was found to be the [0/45]2 stacking sequences. © BEIESP. Blue Eyes Intelligence Engineering and Sciences Publication 2019-07 Article PeerReviewed application/pdf en http://irep.iium.edu.my/79862/1/79862_The%20Impact%20Behaviour%20of%20Carbon.pdf application/pdf en http://irep.iium.edu.my/79862/2/79862_The%20Impact%20Behaviour%20of%20Carbon_SCOPUS.pdf Omar, Nurihan and Aminanda, Yulfian and Mohamed Ali, Jaafar Syed and A. Rasid, Zainudin and Yahaya, Hafizal (2019) The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method. International Journal of Recent Technology and Engineering, 8 (2). pp. 2617-2622. ISSN 2277-3878 https://www.ijrte.org/wp-content/uploads/papers/v8i2/B3013078219.pdf 10.35940/ijrte.B3013.078219
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 TK Electrical engineering. Electronics Nuclear engineering
spellingShingle TK Electrical engineering. Electronics Nuclear engineering
Omar, Nurihan
Aminanda, Yulfian
Mohamed Ali, Jaafar Syed
A. Rasid, Zainudin
Yahaya, Hafizal
The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method
description Composite material has been widely used in aircrafts due to its high strength to weight ratio that leads to weight saving of the aircrafts. Equally important, aircraft material should be tough i.e. it should have the ability to absorb high energy and thus resist fracture. The aircraft’s wing design requires the material to have high toughness as parts of the wing especially its leading edge is subjected to impact loadings. Using finite element software of LS-DYNA, this research focuses on studying the impact behaviour of composite panels that represent the leading edges of wings when the panels are subjected to rigid sphere projectile. Three shapes of panels are used: flat, semi-circular and semi ellipse while panels can be of 2, 4 and 8 layers to vary its thickness. The panels are made of laminated composites with woven carbon fibres and the angle of orientations are [0/90] n, [0/45]n and [45/-45]n where n will give the number of layer for the composite. The Mat-58 material type suitable for woven type fibre is used where failure criteria of Hashin is applied. It was found that the simulation results are in a very close agreement with the finding from experiments conducted earlier. Furthermore, the optimum stacking sequence was found to be the [0/45]2 stacking sequences. © BEIESP.
format Article
author Omar, Nurihan
Aminanda, Yulfian
Mohamed Ali, Jaafar Syed
A. Rasid, Zainudin
Yahaya, Hafizal
author_facet Omar, Nurihan
Aminanda, Yulfian
Mohamed Ali, Jaafar Syed
A. Rasid, Zainudin
Yahaya, Hafizal
author_sort Omar, Nurihan
title The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method
title_short The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method
title_full The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method
title_fullStr The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method
title_full_unstemmed The impact behaviour of carbon fiber-epoxy composite leading edge using finite element method
title_sort impact behaviour of carbon fiber-epoxy composite leading edge using finite element method
publisher Blue Eyes Intelligence Engineering and Sciences Publication
publishDate 2019
url http://irep.iium.edu.my/79862/1/79862_The%20Impact%20Behaviour%20of%20Carbon.pdf
http://irep.iium.edu.my/79862/2/79862_The%20Impact%20Behaviour%20of%20Carbon_SCOPUS.pdf
http://irep.iium.edu.my/79862/
https://www.ijrte.org/wp-content/uploads/papers/v8i2/B3013078219.pdf
_version_ 1662753904967811072
score 13.211869

Similar Items