Finite element analysis of cracks in aging aircraft structures with bonded composite-patch repairs
Bonded composite-patch repair has been used to transfer load from cracked structures to the reinforcement such that subsequent crack propagation is reduced. In this study, the mechanical behavior of a single edge v-notch Al7075-T6 plate repaired with 1-ply and 4-ply composite patches was investigate...
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| Veröffentlicht in: | Composites. Part B, Engineering Engineering, 2011-04, Vol.42 (3), p.505-510 |
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| container_title | Composites. Part B, Engineering |
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| creator | Gu, Linxia Kasavajhala, Ananth Ram Mahanth Zhao, Shijia |
| description | Bonded composite-patch repair has been used to transfer load from cracked structures to the reinforcement such that subsequent crack propagation is reduced. In this study, the mechanical behavior of a single edge v-notch Al7075-T6 plate repaired with 1-ply and 4-ply composite patches was investigated through the finite element method. Contour integral method was used to define and evaluate the stress intensity factors at the crack tip. The effect of the adhesive epoxy film, patch material, thickness and ply orientations on the evolution of the stress intensity factor (SIF) of the repaired structure was examined. The results indicated that the SIF of the notched plate is reduced by 1/6–1/20 as a result of the bonded composite-patch repair. The crack mouth opening displacement (CMOD) is reduced even further by 80–83%. Shear strength and thickness of the adhesive bond were the largest factors in the effectiveness of patch repair. |
| doi_str_mv | 10.1016/j.compositesb.2010.11.014 |
| format | Article |
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In this study, the mechanical behavior of a single edge v-notch Al7075-T6 plate repaired with 1-ply and 4-ply composite patches was investigated through the finite element method. Contour integral method was used to define and evaluate the stress intensity factors at the crack tip. The effect of the adhesive epoxy film, patch material, thickness and ply orientations on the evolution of the stress intensity factor (SIF) of the repaired structure was examined. The results indicated that the SIF of the notched plate is reduced by 1/6–1/20 as a result of the bonded composite-patch repair. The crack mouth opening displacement (CMOD) is reduced even further by 80–83%. Shear strength and thickness of the adhesive bond were the largest factors in the effectiveness of patch repair.</description><identifier>ISSN: 1359-8368</identifier><identifier>EISSN: 1879-1069</identifier><identifier>DOI: 10.1016/j.compositesb.2010.11.014</identifier><language>eng</language><publisher>Kidlington: Elsevier Ltd</publisher><subject>A. Lamina/ply ; Adhesive bonding ; aircraft ; Aircraft industry. Spacecraft ; Aluminum base alloys ; Application fields ; Applications ; Applied sciences ; B. Adhesion ; B. Stress transfer ; Bonding ; C. Finite element analysis ; Cracks ; Engineering techniques in metallurgy. Applications. Other aspects ; epoxides ; Exact sciences and technology ; finite element analysis ; Maintenance ; Mathematical analysis ; Metals. Metallurgy ; Plates (structural members) ; Polymer industry, paints, wood ; Repairing ; shear strength ; Stress intensity factor ; Technology of polymers</subject><ispartof>Composites. Part B, Engineering, 2011-04, Vol.42 (3), p.505-510</ispartof><rights>2010 Elsevier Ltd</rights><rights>2015 INIST-CNRS</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c491t-6bba4c7ca03749768381eda0543f83018ac462644586fda5fc4ae312f7872c203</citedby><cites>FETCH-LOGICAL-c491t-6bba4c7ca03749768381eda0543f83018ac462644586fda5fc4ae312f7872c203</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://dx.doi.org/10.1016/j.compositesb.2010.11.014$$EHTML$$P50$$Gelsevier$$H</linktohtml><link.rule.ids>314,780,784,3550,27924,27925,45995</link.rule.ids><backlink>$$Uhttp://pascal-francis.inist.fr/vibad/index.php?action=getRecordDetail&idt=23861484$$DView record in Pascal Francis$$Hfree_for_read</backlink></links><search><creatorcontrib>Gu, Linxia</creatorcontrib><creatorcontrib>Kasavajhala, Ananth Ram Mahanth</creatorcontrib><creatorcontrib>Zhao, Shijia</creatorcontrib><title>Finite element analysis of cracks in aging aircraft structures with bonded composite-patch repairs</title><title>Composites. Part B, Engineering</title><description>Bonded composite-patch repair has been used to transfer load from cracked structures to the reinforcement such that subsequent crack propagation is reduced. In this study, the mechanical behavior of a single edge v-notch Al7075-T6 plate repaired with 1-ply and 4-ply composite patches was investigated through the finite element method. Contour integral method was used to define and evaluate the stress intensity factors at the crack tip. The effect of the adhesive epoxy film, patch material, thickness and ply orientations on the evolution of the stress intensity factor (SIF) of the repaired structure was examined. The results indicated that the SIF of the notched plate is reduced by 1/6–1/20 as a result of the bonded composite-patch repair. The crack mouth opening displacement (CMOD) is reduced even further by 80–83%. Shear strength and thickness of the adhesive bond were the largest factors in the effectiveness of patch repair.</description><subject>A. Lamina/ply</subject><subject>Adhesive bonding</subject><subject>aircraft</subject><subject>Aircraft industry. Spacecraft</subject><subject>Aluminum base alloys</subject><subject>Application fields</subject><subject>Applications</subject><subject>Applied sciences</subject><subject>B. Adhesion</subject><subject>B. Stress transfer</subject><subject>Bonding</subject><subject>C. Finite element analysis</subject><subject>Cracks</subject><subject>Engineering techniques in metallurgy. Applications. Other aspects</subject><subject>epoxides</subject><subject>Exact sciences and technology</subject><subject>finite element analysis</subject><subject>Maintenance</subject><subject>Mathematical analysis</subject><subject>Metals. Metallurgy</subject><subject>Plates (structural members)</subject><subject>Polymer industry, paints, wood</subject><subject>Repairing</subject><subject>shear strength</subject><subject>Stress intensity factor</subject><subject>Technology of polymers</subject><issn>1359-8368</issn><issn>1879-1069</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2011</creationdate><recordtype>article</recordtype><recordid>eNqNkU1v1DAQhiMEEqXwGzAHBJcs_ortHNGqBaRKHKBna-KMt16ySfB4Qf33eLVVxQlxsjV63tcjP03zRvCN4MJ82G_CclgXSgVp2Eh-mosNF_pJcyGc7VvBTf-03lXXt04Z97x5QbTnnOtOyYtmuE5zzTKc8IBzYTDDdE-J2BJZyBB-EEszg12adwxSrqNYGJV8DOWYkdjvVO7YsMwjjuxxk3aFEu5YxrVG6GXzLMJE-OrhvGxur6--bz-3N18_fdl-vGmD7kVpzTCADjYAV1b31jjlBI7AO62iU1w4CNpIo3XnTByhi0EDKiGjdVYGydVl8-7cu-bl5xGp-EOigNMEMy5H8s5o1SvubCXf_5MU1nKlubSyov0ZDXkhyhj9mtMB8r0X3J8M-L3_y4A_GfBC-GqgZt8-PAMUYIoZ5pDosUAqZ4R2J-71mYuweNjlytx-q0VdtaR070wltmcC6__9Spg9hYRzwDFlDMWPS_qPff4ADjysNA</recordid><startdate>20110401</startdate><enddate>20110401</enddate><creator>Gu, Linxia</creator><creator>Kasavajhala, Ananth Ram Mahanth</creator><creator>Zhao, Shijia</creator><general>Elsevier Ltd</general><general>Elsevier</general><scope>FBQ</scope><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7QF</scope><scope>7SR</scope><scope>7TB</scope><scope>8BQ</scope><scope>8FD</scope><scope>FR3</scope><scope>H8D</scope><scope>JG9</scope><scope>KR7</scope><scope>L7M</scope></search><sort><creationdate>20110401</creationdate><title>Finite element analysis of cracks in aging aircraft structures with bonded composite-patch repairs</title><author>Gu, Linxia ; Kasavajhala, Ananth Ram Mahanth ; Zhao, Shijia</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c491t-6bba4c7ca03749768381eda0543f83018ac462644586fda5fc4ae312f7872c203</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2011</creationdate><topic>A. 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Metallurgy</topic><topic>Plates (structural members)</topic><topic>Polymer industry, paints, wood</topic><topic>Repairing</topic><topic>shear strength</topic><topic>Stress intensity factor</topic><topic>Technology of polymers</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Gu, Linxia</creatorcontrib><creatorcontrib>Kasavajhala, Ananth Ram Mahanth</creatorcontrib><creatorcontrib>Zhao, Shijia</creatorcontrib><collection>AGRIS</collection><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Aluminium Industry Abstracts</collection><collection>Engineered Materials Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>METADEX</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Materials Research Database</collection><collection>Civil Engineering Abstracts</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Composites. 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| ispartof | Composites. Part B, Engineering, 2011-04, Vol.42 (3), p.505-510 |
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| source | ScienceDirect Journals (5 years ago - present) |
| subjects | A. Lamina/ply Adhesive bonding aircraft Aircraft industry. Spacecraft Aluminum base alloys Application fields Applications Applied sciences B. Adhesion B. Stress transfer Bonding C. Finite element analysis Cracks Engineering techniques in metallurgy. Applications. Other aspects epoxides Exact sciences and technology finite element analysis Maintenance Mathematical analysis Metals. Metallurgy Plates (structural members) Polymer industry, paints, wood Repairing shear strength Stress intensity factor Technology of polymers |
| title | Finite element analysis of cracks in aging aircraft structures with bonded composite-patch repairs |
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