On the static strength of aluminium and carbon fibre aircraft lap joint repairs

The behaviour of various aircraft lap joint repair configurations is investigated experimentally and numerically under static loading. The lap joints consist of aluminium alloy (AA) 2024-T3 substrates repaired with twin single-sided AA 2024-T3 or Carbon Fibre Reinforced Epoxy (CFRE) doublers. Pure r...

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Autores: Pitta, Siddharth|||0000-0001-5247-9648, de la Mora Carles, Victor, Roure Fernández, Francisco|||0000-0001-9521-7429, Crespo Artiaga, Daniel|||0000-0003-1743-2400, Rojas Gregorio, José Ignacio|||0000-0002-7025-4378
Tipo de recurso: artículo
Fecha de publicación:2018
País:España
Institución:Universitat Politècnica de Catalunya (UPC)
Repositorio:UPCommons. Portal del coneixement obert de la UPC
Idioma:inglés
OAI Identifier:oai:upcommons.upc.edu:2117/118582
Acceso en línea:https://hdl.handle.net/2117/118582
https://dx.doi.org/10.1016/j.compstruct.2018.06.002
Access Level:acceso abierto
Palabra clave:Airplanes -- Maintenance and repair
Aluminum alloys
Aircraft lap joint
Aluminium alloy
Carbon fibre reinforced epoxy
Rivet
Adhesive
Finite element analysis
Avions -- Manteniment i reparació
Alumini -- Aliatges
Àrees temàtiques de la UPC::Física
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spelling On the static strength of aluminium and carbon fibre aircraft lap joint repairsPitta, Siddharth|||0000-0001-5247-9648de la Mora Carles, VictorRoure Fernández, Francisco|||0000-0001-9521-7429Crespo Artiaga, Daniel|||0000-0003-1743-2400Rojas Gregorio, José Ignacio|||0000-0002-7025-4378Airplanes -- Maintenance and repairAluminum alloysAircraft lap jointAluminium alloyCarbon fibre reinforced epoxyRivetAdhesiveFinite element analysisAvions -- Manteniment i reparacióAlumini -- AliatgesÀrees temàtiques de la UPC::FísicaThe behaviour of various aircraft lap joint repair configurations is investigated experimentally and numerically under static loading. The lap joints consist of aluminium alloy (AA) 2024-T3 substrates repaired with twin single-sided AA 2024-T3 or Carbon Fibre Reinforced Epoxy (CFRE) doublers. Pure riveted, pure bonded and hybrid (riveted and bonded) joints of metal–metal and metal–composite configurations are investigated. From experimental results, joints with adhesive bond showed nearly 5 times higher average strength than pure riveted joints, while hybrid joints performed better than riveted and bonded joints because of higher stiffness. On the other hand, hybrid metal–metal joint has 70% higher average strength compared to hybrid metal–composite joint. Rivet-shear has caused failure of riveted joints, and adhesive failure is observed in pure bonded joints. Hybrid joints with metal doublers have failed initially due to adhesive failure and later rivet shear. Interestingly, net-section failure is observed in composite doublers with breakage of doublers due to the presence of holes in the doublers. Experimental results are complimented with numerical analysis using commercial finite element code ABAQUS. Load–displacement curves obtained from the numerical results are in good agreement with experiments with a marginal error of 2%. In addition to load–displacement curves, a detailed stress analysis is performed numerically on metal–metal and metal-composite joints under riveted, bonded and hybrid configurations to study stress distribution on substrate and doublers. Numerical analysis showed hybrid and bonded joints have lower stresses in substrate and doublers compared to the riveted joints. Bonded joints have smoother load transfer due to the adhesive spread over a larger area. And finally, Stress Intensity Factors (SIFs) are performed numerically for unreinforced and reinforced metal substrate with crack length of 1, 5 and 10¿mm with metal and composite doublers under riveted and bonded configuration. For crack of 10¿mm, 35% reduction in SIFs is observed for reinforced substrate with bonded metal or composite doublers compared to unreinforced cracked substrate.Peer Reviewed20182018-10-0120182018-06-27journal articlehttp://purl.org/coar/resource_type/c_6501VoRhttp://purl.org/coar/version/c_970fb48d4fbd8a85info:eu-repo/semantics/articleapplication/pdfhttps://hdl.handle.net/2117/118582https://dx.doi.org/10.1016/j.compstruct.2018.06.002reponame:UPCommons. Portal del coneixement obert de la UPCinstname:Universitat Politècnica de Catalunya (UPC)Inglésengopen accesshttp://purl.org/coar/access_right/c_abf2Attribution-NonCommercial-NoDerivs 3.0 Spainhttp://creativecommons.org/licenses/by-nc-nd/3.0/es/info:eu-repo/semantics/openAccessoai:upcommons.upc.edu:2117/1185822026-05-27T15:37:01Z
dc.title.none.fl_str_mv On the static strength of aluminium and carbon fibre aircraft lap joint repairs
title On the static strength of aluminium and carbon fibre aircraft lap joint repairs
spellingShingle On the static strength of aluminium and carbon fibre aircraft lap joint repairs
Pitta, Siddharth|||0000-0001-5247-9648
Airplanes -- Maintenance and repair
Aluminum alloys
Aircraft lap joint
Aluminium alloy
Carbon fibre reinforced epoxy
Rivet
Adhesive
Finite element analysis
Avions -- Manteniment i reparació
Alumini -- Aliatges
Àrees temàtiques de la UPC::Física
title_short On the static strength of aluminium and carbon fibre aircraft lap joint repairs
title_full On the static strength of aluminium and carbon fibre aircraft lap joint repairs
title_fullStr On the static strength of aluminium and carbon fibre aircraft lap joint repairs
title_full_unstemmed On the static strength of aluminium and carbon fibre aircraft lap joint repairs
title_sort On the static strength of aluminium and carbon fibre aircraft lap joint repairs
dc.creator.none.fl_str_mv Pitta, Siddharth|||0000-0001-5247-9648
de la Mora Carles, Victor
Roure Fernández, Francisco|||0000-0001-9521-7429
Crespo Artiaga, Daniel|||0000-0003-1743-2400
Rojas Gregorio, José Ignacio|||0000-0002-7025-4378
author Pitta, Siddharth|||0000-0001-5247-9648
author_facet Pitta, Siddharth|||0000-0001-5247-9648
de la Mora Carles, Victor
Roure Fernández, Francisco|||0000-0001-9521-7429
Crespo Artiaga, Daniel|||0000-0003-1743-2400
Rojas Gregorio, José Ignacio|||0000-0002-7025-4378
author_role author
author2 de la Mora Carles, Victor
Roure Fernández, Francisco|||0000-0001-9521-7429
Crespo Artiaga, Daniel|||0000-0003-1743-2400
Rojas Gregorio, José Ignacio|||0000-0002-7025-4378
author2_role author
author
author
author
dc.subject.none.fl_str_mv Airplanes -- Maintenance and repair
Aluminum alloys
Aircraft lap joint
Aluminium alloy
Carbon fibre reinforced epoxy
Rivet
Adhesive
Finite element analysis
Avions -- Manteniment i reparació
Alumini -- Aliatges
Àrees temàtiques de la UPC::Física
topic Airplanes -- Maintenance and repair
Aluminum alloys
Aircraft lap joint
Aluminium alloy
Carbon fibre reinforced epoxy
Rivet
Adhesive
Finite element analysis
Avions -- Manteniment i reparació
Alumini -- Aliatges
Àrees temàtiques de la UPC::Física
description The behaviour of various aircraft lap joint repair configurations is investigated experimentally and numerically under static loading. The lap joints consist of aluminium alloy (AA) 2024-T3 substrates repaired with twin single-sided AA 2024-T3 or Carbon Fibre Reinforced Epoxy (CFRE) doublers. Pure riveted, pure bonded and hybrid (riveted and bonded) joints of metal–metal and metal–composite configurations are investigated. From experimental results, joints with adhesive bond showed nearly 5 times higher average strength than pure riveted joints, while hybrid joints performed better than riveted and bonded joints because of higher stiffness. On the other hand, hybrid metal–metal joint has 70% higher average strength compared to hybrid metal–composite joint. Rivet-shear has caused failure of riveted joints, and adhesive failure is observed in pure bonded joints. Hybrid joints with metal doublers have failed initially due to adhesive failure and later rivet shear. Interestingly, net-section failure is observed in composite doublers with breakage of doublers due to the presence of holes in the doublers. Experimental results are complimented with numerical analysis using commercial finite element code ABAQUS. Load–displacement curves obtained from the numerical results are in good agreement with experiments with a marginal error of 2%. In addition to load–displacement curves, a detailed stress analysis is performed numerically on metal–metal and metal-composite joints under riveted, bonded and hybrid configurations to study stress distribution on substrate and doublers. Numerical analysis showed hybrid and bonded joints have lower stresses in substrate and doublers compared to the riveted joints. Bonded joints have smoother load transfer due to the adhesive spread over a larger area. And finally, Stress Intensity Factors (SIFs) are performed numerically for unreinforced and reinforced metal substrate with crack length of 1, 5 and 10¿mm with metal and composite doublers under riveted and bonded configuration. For crack of 10¿mm, 35% reduction in SIFs is observed for reinforced substrate with bonded metal or composite doublers compared to unreinforced cracked substrate.
publishDate 2018
dc.date.none.fl_str_mv 2018
2018-10-01
2018
2018-06-27
dc.type.none.fl_str_mv journal article
http://purl.org/coar/resource_type/c_6501
VoR
http://purl.org/coar/version/c_970fb48d4fbd8a85
dc.type.openaire.fl_str_mv info:eu-repo/semantics/article
format article
dc.identifier.none.fl_str_mv https://hdl.handle.net/2117/118582
https://dx.doi.org/10.1016/j.compstruct.2018.06.002
url https://hdl.handle.net/2117/118582
https://dx.doi.org/10.1016/j.compstruct.2018.06.002
dc.language.none.fl_str_mv Inglés
eng
language_invalid_str_mv Inglés
language eng
dc.rights.none.fl_str_mv open access
http://purl.org/coar/access_right/c_abf2
Attribution-NonCommercial-NoDerivs 3.0 Spain
http://creativecommons.org/licenses/by-nc-nd/3.0/es/
dc.rights.openaire.fl_str_mv info:eu-repo/semantics/openAccess
rights_invalid_str_mv open access
http://purl.org/coar/access_right/c_abf2
Attribution-NonCommercial-NoDerivs 3.0 Spain
http://creativecommons.org/licenses/by-nc-nd/3.0/es/
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv application/pdf
dc.source.none.fl_str_mv reponame:UPCommons. Portal del coneixement obert de la UPC
instname:Universitat Politècnica de Catalunya (UPC)
instname_str Universitat Politècnica de Catalunya (UPC)
reponame_str UPCommons. Portal del coneixement obert de la UPC
collection UPCommons. Portal del coneixement obert de la UPC
repository.name.fl_str_mv
repository.mail.fl_str_mv
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score 15,300719

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