Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge

The existing hinge bracket for aircraft spoilers is mostly made of metallic materials. The change of the materials of the hinge bracket from metallic to composites can contribute to a low weight structure. The demand for fibre-reinforced plastic (FRP) composites in aircraft industries especially the...

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Main Author:	Abdullah, Zailinda
Format:	Thesis
Language:	English English
Published:	2019
Subjects:	T Technology (General)
Online Access:	http://eprints.utem.edu.my/id/eprint/24502/1/Mechanical%20Behaviour%20Of%20Carbon%20Reinforced%20Polymer%20Using%20RTM%20And%20VIP%20Techniques%20For%20Aircraft%20Spoiler%20Hinge.pdf http://eprints.utem.edu.my/id/eprint/24502/2/Mechanical%20Behaviour%20Of%20Carbon%20Reinforced%20Polymer%20Using%20RTM%20And%20VIP%20Techniques%20For%20Aircraft%20Spoiler%20Hinge.pdf
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id	my-utem-ep.24502
record_format	uketd_dc
institution	Universiti Teknikal Malaysia Melaka
collection	UTeM Repository
language	English English
topic	T Technology (General) T Technology (General)
spellingShingle	T Technology (General) T Technology (General) Abdullah, Zailinda Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge
description	The existing hinge bracket for aircraft spoilers is mostly made of metallic materials. The change of the materials of the hinge bracket from metallic to composites can contribute to a low weight structure. The demand for fibre-reinforced plastic (FRP) composites in aircraft industries especially the hinge bracket for spoilers is increasing over the years. However, the current fabrication process for aircraft hinge brackets used as spoilers incurred high costs in terms of tooling, production, and testing cost. Therefore, in this thesis, flat panel with different number and orientation of woven carbon fibre layers in laminated composites system were used to determine its mechanical behaviour. Two different processes have been used, namely Resin Transfer Moulding Process (RTM) and Vacuum Infusion Process (VIP). The fabrication processes were used to fabricate FRP composite with different plies as parameters. The parameters used were 8, 16, 24 and 32 plies of woven carbon fibres. Besides that, the orientation of the carbon fibre remains constant which are [0/90]n and [45/-45]n. For the mechanical test, these FRP composites undergo tensile tests and flexural tests. From the experiment, it is shown that 8CF/EP composites fabricated using VIP have 10.6 % higher in specific strength obtained from the tensile test and 64.4 % higher in specific strength obtained from the flexural test. It is also indicated that the composites with 8 plies of carbon FRP composite fabricated by using VIP gave good tensile and flexural strength compared to the composites fabricated by using the RTM method. Moreover, 8 plies of carbon FRP gave better mechanical properties compared to other different plies of carbon FRP composite. A comparison of mechanical properties between FRP composites made by VIP with existing hinge for aircraft spoiler shows that the UTS of FRP composites is 58% lower than existing material; AA7075-T651.
format	Thesis
qualification_name	Master of Philosophy (M.Phil.)
qualification_level	Master's degree
author	Abdullah, Zailinda
author_facet	Abdullah, Zailinda
author_sort	Abdullah, Zailinda
title	Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge
title_short	Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge
title_full	Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge
title_fullStr	Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge
title_full_unstemmed	Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge
title_sort	mechanical behaviour of carbon reinforced polymer using rtm and vip techniques for aircraft spoiler hinge
granting_institution	Universiti Teknikal Malaysia Melaka
granting_department	Faculty Of Mechanical Engineering
publishDate	2019
url	http://eprints.utem.edu.my/id/eprint/24502/1/Mechanical%20Behaviour%20Of%20Carbon%20Reinforced%20Polymer%20Using%20RTM%20And%20VIP%20Techniques%20For%20Aircraft%20Spoiler%20Hinge.pdf http://eprints.utem.edu.my/id/eprint/24502/2/Mechanical%20Behaviour%20Of%20Carbon%20Reinforced%20Polymer%20Using%20RTM%20And%20VIP%20Techniques%20For%20Aircraft%20Spoiler%20Hinge.pdf
_version_	1747834069202239488
spelling	my-utem-ep.245022021-10-05T09:34:25Z Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge 2019 Abdullah, Zailinda T Technology (General) TA Engineering (General). Civil engineering (General) The existing hinge bracket for aircraft spoilers is mostly made of metallic materials. The change of the materials of the hinge bracket from metallic to composites can contribute to a low weight structure. The demand for fibre-reinforced plastic (FRP) composites in aircraft industries especially the hinge bracket for spoilers is increasing over the years. However, the current fabrication process for aircraft hinge brackets used as spoilers incurred high costs in terms of tooling, production, and testing cost. Therefore, in this thesis, flat panel with different number and orientation of woven carbon fibre layers in laminated composites system were used to determine its mechanical behaviour. Two different processes have been used, namely Resin Transfer Moulding Process (RTM) and Vacuum Infusion Process (VIP). The fabrication processes were used to fabricate FRP composite with different plies as parameters. The parameters used were 8, 16, 24 and 32 plies of woven carbon fibres. Besides that, the orientation of the carbon fibre remains constant which are [0/90]n and [45/-45]n. For the mechanical test, these FRP composites undergo tensile tests and flexural tests. From the experiment, it is shown that 8CF/EP composites fabricated using VIP have 10.6 % higher in specific strength obtained from the tensile test and 64.4 % higher in specific strength obtained from the flexural test. It is also indicated that the composites with 8 plies of carbon FRP composite fabricated by using VIP gave good tensile and flexural strength compared to the composites fabricated by using the RTM method. Moreover, 8 plies of carbon FRP gave better mechanical properties compared to other different plies of carbon FRP composite. A comparison of mechanical properties between FRP composites made by VIP with existing hinge for aircraft spoiler shows that the UTS of FRP composites is 58% lower than existing material; AA7075-T651. 2019 Thesis http://eprints.utem.edu.my/id/eprint/24502/ http://eprints.utem.edu.my/id/eprint/24502/1/Mechanical%20Behaviour%20Of%20Carbon%20Reinforced%20Polymer%20Using%20RTM%20And%20VIP%20Techniques%20For%20Aircraft%20Spoiler%20Hinge.pdf text en public http://eprints.utem.edu.my/id/eprint/24502/2/Mechanical%20Behaviour%20Of%20Carbon%20Reinforced%20Polymer%20Using%20RTM%20And%20VIP%20Techniques%20For%20Aircraft%20Spoiler%20Hinge.pdf text en validuser https://plh.utem.edu.my/cgi-bin/koha/opac-detail.pl?biblionumber=116902 mphil masters Universiti Teknikal Malaysia Melaka Faculty Of Mechanical Engineering 1. 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Mechanical Behaviour Of Carbon Reinforced Polymer Using RTM And VIP Techniques For Aircraft Spoiler Hinge

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