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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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spelling my.utm.781652018-07-25T08:18:59Z http://eprints.utm.my/id/eprint/78165/ Failure analysis of notched composite plates with bushings 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 NonPeerReviewed application/pdf en http://eprints.utm.my/id/eprint/78165/1/HoomanHooshyarfardMFKM20131.pdf Hooshyarfard, Hooman (2013) Failure analysis of notched composite plates with bushings. Masters thesis, Universiti Teknologi Malaysia, Faculty of Mechanical Engineering. http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:79552
institution Universiti Teknologi Malaysia
building UTM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Malaysia
content_source UTM Institutional Repository
url_provider http://eprints.utm.my/
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
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
publishDate 2013
url http://eprints.utm.my/id/eprint/78165/1/HoomanHooshyarfardMFKM20131.pdf
http://eprints.utm.my/id/eprint/78165/
http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:79552
_version_ 1643657747241107456
score 13.211869

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