Failure analysis of notched composite plates with bushings

Fiber reinforced composite structures are widely used in the aerospace, aircraft, civil and automotive applications due to their high specific modulus and high specific strength. These applications require the joining of the composite structures. In mechanically fastened joints holes should be drill...

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Main Author:	Hooshyarfard, Hooman
Format:	Thesis
Language:	English
Published:	2013
Subjects:	TJ Mechanical engineering and machinery
Online Access:	http://eprints.utm.my/id/eprint/78165/1/HoomanHooshyarfardMFKM20131.pdf
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id	my-utm-ep.78165
record_format	uketd_dc
spelling	my-utm-ep.781652018-07-25T08:18:59Z Failure analysis of notched composite plates with bushings 2013-01 Hooshyarfard, Hooman TJ Mechanical engineering and machinery Fiber reinforced composite structures are widely used in the aerospace, aircraft, civil and automotive applications due to their high specific modulus and high specific strength. These applications require the joining of the composite structures. In mechanically fastened joints holes should be drilled, and the stress concentration around the holes leads to significant reduction in the strength of composite laminates. Bushings are installed to improve the strength of the laminates. Based on finite element calculations, the effect of bushing installation on the failure characteristics of laminates was investigated in this thesis. The Tsai-Wu failure criterion was used for failure calculations. A carbon epoxy laminate subjected to 0.4 mm pin displacement was simulated through different models with and without bushing. Also, the established samples had different orientations which were [0 45 -45 90]s and [90 45 -45 0]s in order to study the influence of stacking sequence of layers on the laminate strength. The results showed a great improvement in load carrying capacity of samples with bushing due to the introduced bushing compressive load which postponed the failure. Moreover, the laminate with bushing and [90 45 -45 0]s orientation showed higher strength compared to the [0 45 -45 90]s laminate. The obtained results of the laminate orientation effect were matched with experimental test results. 2013-01 Thesis http://eprints.utm.my/id/eprint/78165/ http://eprints.utm.my/id/eprint/78165/1/HoomanHooshyarfardMFKM20131.pdf application/pdf en public http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:79552 masters Universiti Teknologi Malaysia, Faculty of Mechanical Engineering Faculty of Mechanical Engineering
institution	Universiti Teknologi Malaysia
collection	UTM Institutional Repository
language	English
topic	TJ Mechanical engineering and machinery
spellingShingle	TJ Mechanical engineering and machinery Hooshyarfard, Hooman Failure analysis of notched composite plates with bushings
description	Fiber reinforced composite structures are widely used in the aerospace, aircraft, civil and automotive applications due to their high specific modulus and high specific strength. These applications require the joining of the composite structures. In mechanically fastened joints holes should be drilled, and the stress concentration around the holes leads to significant reduction in the strength of composite laminates. Bushings are installed to improve the strength of the laminates. Based on finite element calculations, the effect of bushing installation on the failure characteristics of laminates was investigated in this thesis. The Tsai-Wu failure criterion was used for failure calculations. A carbon epoxy laminate subjected to 0.4 mm pin displacement was simulated through different models with and without bushing. Also, the established samples had different orientations which were [0 45 -45 90]s and [90 45 -45 0]s in order to study the influence of stacking sequence of layers on the laminate strength. The results showed a great improvement in load carrying capacity of samples with bushing due to the introduced bushing compressive load which postponed the failure. Moreover, the laminate with bushing and [90 45 -45 0]s orientation showed higher strength compared to the [0 45 -45 90]s laminate. The obtained results of the laminate orientation effect were matched with experimental test results.
format	Thesis
qualification_level	Master's degree
author	Hooshyarfard, Hooman
author_facet	Hooshyarfard, Hooman
author_sort	Hooshyarfard, Hooman
title	Failure analysis of notched composite plates with bushings
title_short	Failure analysis of notched composite plates with bushings
title_full	Failure analysis of notched composite plates with bushings
title_fullStr	Failure analysis of notched composite plates with bushings
title_full_unstemmed	Failure analysis of notched composite plates with bushings
title_sort	failure analysis of notched composite plates with bushings
granting_institution	Universiti Teknologi Malaysia, Faculty of Mechanical Engineering
granting_department	Faculty of Mechanical Engineering
publishDate	2013
url	http://eprints.utm.my/id/eprint/78165/1/HoomanHooshyarfardMFKM20131.pdf
_version_	1747817922928050176

Failure analysis of notched composite plates with bushings

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