The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading
One of major concerns that related to the flight safety is impact of birds. To minimize the risks, there is need to increase the impact resistance of aircraft by developing a new material and has the good structural design of aircraft structures. The hybrid laminates are potential candidate material...
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| Format: | Conference or Workshop Item |
| Language: | English |
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IOP Publishing
2017
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| Online Access: | http://umpir.ump.edu.my/id/eprint/19169/ http://umpir.ump.edu.my/id/eprint/19169/1/The%20Behavior%20Of%20Aluminium%20Carbon-Epoxy%20Fibre%20Metal%20Laminate%20Under%20Quasi-Static%20Loading.pdf |
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| author | Nur Khaleeda, Romli M. R. M., Rejab Bachtiar, Dandi Siregar, J. P. M. F., Rani W. S., Wan Harun Salwani, Mohd Salleh Mohamad Nazirul Mubin, Merzuki |
| author_facet | Nur Khaleeda, Romli M. R. M., Rejab Bachtiar, Dandi Siregar, J. P. M. F., Rani W. S., Wan Harun Salwani, Mohd Salleh Mohamad Nazirul Mubin, Merzuki |
| author_sort | Nur Khaleeda, Romli |
| building | UMP Institutional Repository |
| collection | Online Access |
| description | One of major concerns that related to the flight safety is impact of birds. To minimize the risks, there is need to increase the impact resistance of aircraft by developing a new material and has the good structural design of aircraft structures. The hybrid laminates are potential candidate material to be applied for the aircraft structures susceptible to bird strikes. The fibre metal laminate was fabricated by a compression moulding technique. The carbon fibre and aluminium alloy 2024-0 was laminated by using thermoset epoxy. A compression moulding technique was used for the FML fabrication. The aluminium sheet metal has been roughening by a metal sanding method which to improve the bonding between the fibre and metal layer. The main objective of this paper is to determine the failure response of the laminate under five variations of the crosshead displacement in the quasi-static loading. The FML was modelled and analysed by using Explicit solver. Based on the experimental data of the quasi-static test, the result of 1 mm/min was 11.85 kN and higher than 5, 10, 50 and 100 mm/min which because of the aluminium ductility during the impact loading response. The numerical simulations were generally in good agreement with the experimental measurements. |
| first_indexed | 2025-11-15T02:15:56Z |
| format | Conference or Workshop Item |
| id | ump-19169 |
| institution | Universiti Malaysia Pahang |
| institution_category | Local University |
| language | English |
| last_indexed | 2025-11-15T02:15:56Z |
| publishDate | 2017 |
| publisher | IOP Publishing |
| recordtype | eprints |
| repository_type | Digital Repository |
| spelling | ump-191692018-01-11T00:02:37Z http://umpir.ump.edu.my/id/eprint/19169/ The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading Nur Khaleeda, Romli M. R. M., Rejab Bachtiar, Dandi Siregar, J. P. M. F., Rani W. S., Wan Harun Salwani, Mohd Salleh Mohamad Nazirul Mubin, Merzuki TJ Mechanical engineering and machinery One of major concerns that related to the flight safety is impact of birds. To minimize the risks, there is need to increase the impact resistance of aircraft by developing a new material and has the good structural design of aircraft structures. The hybrid laminates are potential candidate material to be applied for the aircraft structures susceptible to bird strikes. The fibre metal laminate was fabricated by a compression moulding technique. The carbon fibre and aluminium alloy 2024-0 was laminated by using thermoset epoxy. A compression moulding technique was used for the FML fabrication. The aluminium sheet metal has been roughening by a metal sanding method which to improve the bonding between the fibre and metal layer. The main objective of this paper is to determine the failure response of the laminate under five variations of the crosshead displacement in the quasi-static loading. The FML was modelled and analysed by using Explicit solver. Based on the experimental data of the quasi-static test, the result of 1 mm/min was 11.85 kN and higher than 5, 10, 50 and 100 mm/min which because of the aluminium ductility during the impact loading response. The numerical simulations were generally in good agreement with the experimental measurements. IOP Publishing 2017 Conference or Workshop Item PeerReviewed application/pdf en cc_by http://umpir.ump.edu.my/id/eprint/19169/1/The%20Behavior%20Of%20Aluminium%20Carbon-Epoxy%20Fibre%20Metal%20Laminate%20Under%20Quasi-Static%20Loading.pdf Nur Khaleeda, Romli and M. R. M., Rejab and Bachtiar, Dandi and Siregar, J. P. and M. F., Rani and W. S., Wan Harun and Salwani, Mohd Salleh and Mohamad Nazirul Mubin, Merzuki (2017) The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading. In: 4th International Conference on Mechanical Engineering Research (ICMER2017) , 1–2 August 2017 , Swiss Garden Beach Resort, Kuantan, Pahang, Malaysia. pp. 1-12., 257 (012046). ISSN 1757-8981 (Print); 1757-899X (Online) (Published) https://doi.org/10.1088/1757-899X/257/1/012046 doi: 10.1088/1757-899X/257/1/012046 |
| spellingShingle | TJ Mechanical engineering and machinery Nur Khaleeda, Romli M. R. M., Rejab Bachtiar, Dandi Siregar, J. P. M. F., Rani W. S., Wan Harun Salwani, Mohd Salleh Mohamad Nazirul Mubin, Merzuki The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading |
| title | The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading |
| title_full | The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading |
| title_fullStr | The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading |
| title_full_unstemmed | The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading |
| title_short | The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading |
| title_sort | behavior of aluminium carbon/epoxy fibre metal laminate under quasi-static loading |
| topic | TJ Mechanical engineering and machinery |
| url | http://umpir.ump.edu.my/id/eprint/19169/ http://umpir.ump.edu.my/id/eprint/19169/ http://umpir.ump.edu.my/id/eprint/19169/ http://umpir.ump.edu.my/id/eprint/19169/1/The%20Behavior%20Of%20Aluminium%20Carbon-Epoxy%20Fibre%20Metal%20Laminate%20Under%20Quasi-Static%20Loading.pdf |