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...

Full description

Bibliographic Details
Main Authors:	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
Format:	Conference or Workshop Item
Language:	English
Published:	IOP Publishing 2017
Subjects:	TJ Mechanical engineering and machinery
Online Access:	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

id	ump-19169
recordtype	eprints
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) https://doi.org/10.1088/1757-899X/257/1/012046 doi: 10.1088/1757-899X/257/1/012046
repository_type	Digital Repository
institution_category	Local University
institution	Universiti Malaysia Pahang
building	UMP Institutional Repository
collection	Online Access
language	English
topic	TJ Mechanical engineering and machinery
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
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.
format	Conference or Workshop Item
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
title	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_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_sort	behavior of aluminium carbon/epoxy fibre metal laminate under quasi-static loading
publisher	IOP Publishing
publishDate	2017
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
first_indexed	2023-09-18T22:27:28Z
last_indexed	2023-09-18T22:27:28Z
_version_	1777416062888837120

The Behavior Of Aluminium Carbon/Epoxy Fibre Metal Laminate Under Quasi-Static Loading

Similar Items