Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing

This study aimeds at investigating the mechanical behavior of an E-glass fiber-reinforced epoxy resin of a laminated composite sandwich with honeycomb core and a central hole, used in the aeronautics industry submitted to bending loading. Three analytical failure models applied to laminated composit...

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Principais autores:	Silva, Franciélio Gomes da, Freire Júnior, Raimundo Carlos Silverio, Nóbrega, Selma Hissae Shimura da, Dias, Avelino Manuel da Silva
Formato:	article
Idioma:	English
Publicado em:	ABM, ABC, ABPol
Assuntos:	Aeronautical Sandwich Composites Failures Models Bending Test
Endereço do item:	https://repositorio.ufrn.br/handle/123456789/31650
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id	ri-123456789-31650
record_format	dspace
spelling	ri-123456789-316502021-04-05T19:19:11Z Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing Silva, Franciélio Gomes da Freire Júnior, Raimundo Carlos Silverio Nóbrega, Selma Hissae Shimura da Dias, Avelino Manuel da Silva Aeronautical Sandwich Composites Failures Models Bending Test This study aimeds at investigating the mechanical behavior of an E-glass fiber-reinforced epoxy resin of a laminated composite sandwich with honeycomb core and a central hole, used in the aeronautics industry submitted to bending loading. Three analytical failure models applied to laminated composites were compared in order to study the influence of stress concentration due to a central hole. The following criteria were assessed: Average Stress Criterion (ASC), Point Stress Criterion (PSC) and the Inherent Flaw Model (IFM). These models were applied to experimental data obtained in a four-point bending test in samples of the sandwich laminate. Finally, modifications on failure prediction models were proposed and appied in sandwich laminates with a central hole. The results obtained showed the applicability of the proposed formulation and that the suggested changes to the model more adequately fit it to the experimental data 2021-03-03T15:27:09Z 2021-03-03T15:27:09Z 2020-06-01 article SILVA, F. G. da; FREIRE JÚNIOR, R.C. S.; NOBREGA, S. H. S. da; DIAS, A. M. da S.. Application of Failure Criteria in Aeronautical Sandwich Structure Composites with a Central Hole Subjected to Bending Testing. MATERIALS RESEARCH, v. 23, p. 1-7, 2020. Disponível em: https://www.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392020000200216. Acesso em: 21 jan. 2021. http://dx.doi.org/10.1590/1980-5373-mr-2020-0028 1516-1439 1980-5373 https://repositorio.ufrn.br/handle/123456789/31650 10.1590/1980-5373-mr-2020-0028 en Attribution 3.0 Brazil http://creativecommons.org/licenses/by/3.0/br/ application/pdf ABM, ABC, ABPol
institution	Repositório Institucional
collection	RI - UFRN
language	English
topic	Aeronautical Sandwich Composites Failures Models Bending Test
spellingShingle	Aeronautical Sandwich Composites Failures Models Bending Test Silva, Franciélio Gomes da Freire Júnior, Raimundo Carlos Silverio Nóbrega, Selma Hissae Shimura da Dias, Avelino Manuel da Silva Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing
description	This study aimeds at investigating the mechanical behavior of an E-glass fiber-reinforced epoxy resin of a laminated composite sandwich with honeycomb core and a central hole, used in the aeronautics industry submitted to bending loading. Three analytical failure models applied to laminated composites were compared in order to study the influence of stress concentration due to a central hole. The following criteria were assessed: Average Stress Criterion (ASC), Point Stress Criterion (PSC) and the Inherent Flaw Model (IFM). These models were applied to experimental data obtained in a four-point bending test in samples of the sandwich laminate. Finally, modifications on failure prediction models were proposed and appied in sandwich laminates with a central hole. The results obtained showed the applicability of the proposed formulation and that the suggested changes to the model more adequately fit it to the experimental data
format	article
author	Silva, Franciélio Gomes da Freire Júnior, Raimundo Carlos Silverio Nóbrega, Selma Hissae Shimura da Dias, Avelino Manuel da Silva
author_facet	Silva, Franciélio Gomes da Freire Júnior, Raimundo Carlos Silverio Nóbrega, Selma Hissae Shimura da Dias, Avelino Manuel da Silva
author_sort	Silva, Franciélio Gomes da
title	Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing
title_short	Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing
title_full	Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing
title_fullStr	Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing
title_full_unstemmed	Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing
title_sort	application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing
publisher	ABM, ABC, ABPol
publishDate	2021
url	https://repositorio.ufrn.br/handle/123456789/31650
work_keys_str_mv	AT silvafrancieliogomesda applicationoffailurecriteriainaeronauticalsandwichstructurecompositeswithacentralholesubjectedtobendingtesting AT freirejuniorraimundocarlossilverio applicationoffailurecriteriainaeronauticalsandwichstructurecompositeswithacentralholesubjectedtobendingtesting AT nobregaselmahissaeshimurada applicationoffailurecriteriainaeronauticalsandwichstructurecompositeswithacentralholesubjectedtobendingtesting AT diasavelinomanueldasilva applicationoffailurecriteriainaeronauticalsandwichstructurecompositeswithacentralholesubjectedtobendingtesting
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Application of failure criteria in aeronautical sandwich structure composites with a central hole subjected to bending testing

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