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Please use this identifier to cite or link to this item: http://acervodigital.unesp.br/handle/11449/9423
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dc.contributor.authorHilario Cioffi, Maria Odila-
dc.contributor.authorVoorwald, Herman Jacobus Cornelis-
dc.contributor.authorMarin Camargo, Jose Andre-
dc.contributor.authorRezende, Mirabel Cerqueira-
dc.contributor.authorOrtiz, Edmundo C.-
dc.contributor.authorAmbrosio, Luigi-
dc.date.accessioned2014-05-20T13:28:19Z-
dc.date.accessioned2016-10-25T16:48:04Z-
dc.date.available2014-05-20T13:28:19Z-
dc.date.available2016-10-25T16:48:04Z-
dc.date.issued2010-06-15-
dc.identifierhttp://dx.doi.org/10.1016/j.msea.2010.02.054-
dc.identifier.citationMaterials Science and Engineering A-structural Materials Properties Microstructure and Processing. Lausanne: Elsevier B.V. Sa, v. 527, n. 15, p. 3609-3614, 2010.-
dc.identifier.issn0921-5093-
dc.identifier.urihttp://hdl.handle.net/11449/9423-
dc.identifier.urihttp://acervodigital.unesp.br/handle/11449/9423-
dc.description.abstractThe Brazilian industry has shown interest in resin transfer molding process (RTM) to produce aeronautical structural frames with low cost. Literature shows such manufacturing process as adequate to produce simple geometry polymer composite airframes, fairly thickness, requiring high quality of finish without manufacturing scale limitations. An experimental methodology regarding a carbon epoxy composites landing gear sub-component has been developed and a 7050 T7451 stalk was selected to be produced by RTM process. Fatigue sub-scale specimens of intermediate modulus carbon fiber non-crimp multiaxial reinforcement and epoxy mono-component system composite were produced according to ASTM D3039. Axial fatigue tests were carried out according to ASTM D3479 with a sinusoidal load of 10 Hz and load ratio R=0.1. Delamination process occurred independently on the applied load. In order to confirm the replacement advantages, composite properties were compared to those of anodized 7050 T7451 aluminum alloy. (c) 2010 Elsevier B.V. All rights reserved.en
dc.description.sponsorshipConselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)-
dc.description.sponsorshipFundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP)-
dc.format.extent3609-3614-
dc.language.isoeng-
dc.publisherElsevier B.V. Sa-
dc.sourceWeb of Science-
dc.subjectElectron microscopyen
dc.subjectAluminum alloysen
dc.subjectCompositesen
dc.subjectFatigueen
dc.titleFractography analysis and fatigue strength of carbon fiber/RTM6 laminatesen
dc.typeoutro-
dc.contributor.institutionUniversidade Estadual Paulista (UNESP)-
dc.contributor.institutionCTA-
dc.contributor.institutionInstituto Tecnológico de Aeronáutica (ITA)-
dc.contributor.institutionCNR-
dc.description.affiliationUniv Estadual Paulista, Fatigue & Aeronaut Mat Res Grp, UNESP, FEG,DMT, BR-12516410 Guaratingueta, SP, Brazil-
dc.description.affiliationCTA, IAE, Div Mat, BR-12228904 Sao Jose Dos Campos, SP, Brazil-
dc.description.affiliationInst Tecnol Aeronaut, Sao Jose Dos Campos, SP, Brazil-
dc.description.affiliationCNR, Inst Composite & Biomed Mat, I-80125 Naples, Italy-
dc.description.affiliationUnespUniv Estadual Paulista, Fatigue & Aeronaut Mat Res Grp, UNESP, FEG,DMT, BR-12516410 Guaratingueta, SP, Brazil-
dc.description.sponsorshipIdCNPq: 472570/2006-4-
dc.description.sponsorshipIdCNPq: 300233/2006-0-
dc.description.sponsorshipIdCNPq: 301528/2006-0-
dc.description.sponsorshipIdFAPESP: 06/02121-6-
dc.identifier.doi10.1016/j.msea.2010.02.054-
dc.identifier.wosWOS:000277758000045-
dc.rights.accessRightsAcesso restrito-
dc.relation.ispartofMaterials Science and Engineering A: Structural Materials Properties Microstructure and Processing-
Appears in Collections:Artigos, TCCs, Teses e Dissertações da Unesp

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