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...
| Main Authors: | , , , , |
|---|---|
| Format: | Article |
| Language: | English English |
| Published: |
Blue Eyes Intelligence Engineering and Sciences Publication
2019
|
| Subjects: | |
| Online Access: | http://irep.iium.edu.my/79862/ 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 |
| _version_ | 1848788859228258304 |
|---|---|
| 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 |
| building | IIUM Repository |
| collection | Online Access |
| 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. |
| first_indexed | 2025-11-14T17:47:31Z |
| format | Article |
| id | iium-79862 |
| institution | International Islamic University Malaysia |
| institution_category | Local University |
| language | English English |
| last_indexed | 2025-11-14T17:47:31Z |
| publishDate | 2019 |
| publisher | Blue Eyes Intelligence Engineering and Sciences Publication |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | iium-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 |
| 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 |
| title | 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_short | 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 |
| topic | TK Electrical engineering. Electronics Nuclear engineering |
| url | http://irep.iium.edu.my/79862/ http://irep.iium.edu.my/79862/ http://irep.iium.edu.my/79862/ 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 |