Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method

Current hinge brackets for A320 aircraft are made from metallic materials. The change of material from metallic to composite can reduce the structure weight. The classical method of analysis such as hand calculation and actual testing are not recommended for the new composite hinge design because it...

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Main Author:	Razali, Amirul Herman
Format:	Thesis
Language:	English English
Published:	2019
Subjects:	T Technology (General)
Online Access:	http://eprints.utem.edu.my/id/eprint/24508/1/Optimization%20Of%20Composite%20Hinges%20For%20Aircraft%20Spoiler%20Using%20Finite%20Element%20Method.pdf http://eprints.utem.edu.my/id/eprint/24508/2/Optimization%20Of%20Composite%20Hinges%20For%20Aircraft%20Spoiler%20Using%20Finite%20Element%20Method.pdf
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id	my-utem-ep.24508
record_format	uketd_dc
institution	Universiti Teknikal Malaysia Melaka
collection	UTeM Repository
language	English English
advisor	Rivai, Ahmad
topic	T Technology (General) T Technology (General)
spellingShingle	T Technology (General) T Technology (General) Razali, Amirul Herman Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method
description	Current hinge brackets for A320 aircraft are made from metallic materials. The change of material from metallic to composite can reduce the structure weight. The classical method of analysis such as hand calculation and actual testing are not recommended for the new composite hinge design because it leads to high production and testing cost, as well as longer time consumption. This thesis is concerned with the method of modelling and analysing composite hinge bracket for A320 Spoiler using finite element method. The reverse engineering method through MSC PATRAN software is used to benchmark the actual loadings, constraints and allowable stress for the new hinge. Then, the method of optimization using Hypermesh software is used to avoid trial and error method, which requires a lot of efforts and more time. Next, a prototype of composite hinge is developed to validate the weight of the panel. The comparison of results between the old and the new design is done which records a reduction of 32% of the weight. This result proves that the simulation method proposed in this research is indeed feasible to be used for preliminary design stage for the hinge bracket of A320 Spoiler
format	Thesis
qualification_name	Master of Philosophy (M.Phil.)
qualification_level	Master's degree
author	Razali, Amirul Herman
author_facet	Razali, Amirul Herman
author_sort	Razali, Amirul Herman
title	Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method
title_short	Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method
title_full	Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method
title_fullStr	Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method
title_full_unstemmed	Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method
title_sort	optimization of composite hinges for aircraft spoiler using finite element method
granting_institution	Universiti Teknikal Malaysia Melaka
granting_department	Faculty Of Mechaninal Engieering
publishDate	2019
url	http://eprints.utem.edu.my/id/eprint/24508/1/Optimization%20Of%20Composite%20Hinges%20For%20Aircraft%20Spoiler%20Using%20Finite%20Element%20Method.pdf http://eprints.utem.edu.my/id/eprint/24508/2/Optimization%20Of%20Composite%20Hinges%20For%20Aircraft%20Spoiler%20Using%20Finite%20Element%20Method.pdf
_version_	1747834070743646208
spelling	my-utem-ep.245082021-10-05T09:14:33Z Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method 2019 Razali, Amirul Herman T Technology (General) TA Engineering (General). Civil engineering (General) Current hinge brackets for A320 aircraft are made from metallic materials. The change of material from metallic to composite can reduce the structure weight. The classical method of analysis such as hand calculation and actual testing are not recommended for the new composite hinge design because it leads to high production and testing cost, as well as longer time consumption. This thesis is concerned with the method of modelling and analysing composite hinge bracket for A320 Spoiler using finite element method. The reverse engineering method through MSC PATRAN software is used to benchmark the actual loadings, constraints and allowable stress for the new hinge. Then, the method of optimization using Hypermesh software is used to avoid trial and error method, which requires a lot of efforts and more time. Next, a prototype of composite hinge is developed to validate the weight of the panel. The comparison of results between the old and the new design is done which records a reduction of 32% of the weight. This result proves that the simulation method proposed in this research is indeed feasible to be used for preliminary design stage for the hinge bracket of A320 Spoiler 2019 Thesis http://eprints.utem.edu.my/id/eprint/24508/ http://eprints.utem.edu.my/id/eprint/24508/1/Optimization%20Of%20Composite%20Hinges%20For%20Aircraft%20Spoiler%20Using%20Finite%20Element%20Method.pdf text en public http://eprints.utem.edu.my/id/eprint/24508/2/Optimization%20Of%20Composite%20Hinges%20For%20Aircraft%20Spoiler%20Using%20Finite%20Element%20Method.pdf text en validuser https://plh.utem.edu.my/cgi-bin/koha/opac-detail.pl?biblionumber=116908 mphil masters Universiti Teknikal Malaysia Melaka Faculty Of Mechaninal Engieering Rivai, Ahmad 1. Airbus, P. C. 2017. A320 Neo Family sets new standards with 20% reduced fuel burn \| Airbus Press release. 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Optimization Of Composite Hinges For Aircraft Spoiler Using Finite Element Method

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