Analytical formulation of the stress intensity factor for crack emanating from central holes and repaired with bonded composite patch in aircraft structures
The determination of the stress intensity factor at the crack tip is one of the most widely used methods to predict the fatigue life of aircraft structures. This prediction is more complicated for repaired cracks with bonded composite patch. This study was performed in order to establish an analytic...
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| Veröffentlicht in: | Composites. Part B, Engineering Engineering, 2013-02, Vol.45 (1), p.852-857 |
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| container_title | Composites. Part B, Engineering |
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| creator | Albedah, A. Benyahia, F. Dinar, H. Bachir Bouiadjra, B. |
| description | The determination of the stress intensity factor at the crack tip is one of the most widely used methods to predict the fatigue life of aircraft structures. This prediction is more complicated for repaired cracks with bonded composite patch. This study was performed in order to establish an analytical model for the stress intensity factor for repaired crack emanating from central holes. The model was developed by modifying that of Kujawski initially developed for cracks emanating from notch without repair. The obtained results were compared with those calculated with the finite element method and the model of Jones et al. It was found that our model gives a good approximation of the stress intensity factor for repaired crack emanating from central elliptical and circular holes if the results of the finite element analysis are taken as references. |
| doi_str_mv | 10.1016/j.compositesb.2012.08.019 |
| format | Article |
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This prediction is more complicated for repaired cracks with bonded composite patch. This study was performed in order to establish an analytical model for the stress intensity factor for repaired crack emanating from central holes. The model was developed by modifying that of Kujawski initially developed for cracks emanating from notch without repair. The obtained results were compared with those calculated with the finite element method and the model of Jones et al. It was found that our model gives a good approximation of the stress intensity factor for repaired crack emanating from central elliptical and circular holes if the results of the finite element analysis are taken as references.</description><identifier>ISSN: 1359-8368</identifier><identifier>EISSN: 1879-1069</identifier><identifier>DOI: 10.1016/j.compositesb.2012.08.019</identifier><language>eng</language><publisher>Kidlington: Elsevier Ltd</publisher><subject>A. 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Part B, Engineering</title><description>The determination of the stress intensity factor at the crack tip is one of the most widely used methods to predict the fatigue life of aircraft structures. This prediction is more complicated for repaired cracks with bonded composite patch. This study was performed in order to establish an analytical model for the stress intensity factor for repaired crack emanating from central holes. The model was developed by modifying that of Kujawski initially developed for cracks emanating from notch without repair. The obtained results were compared with those calculated with the finite element method and the model of Jones et al. It was found that our model gives a good approximation of the stress intensity factor for repaired crack emanating from central elliptical and circular holes if the results of the finite element analysis are taken as references.</description><subject>A. Layered structures</subject><subject>Aircraft components</subject><subject>Aircraft structures</subject><subject>Applied sciences</subject><subject>B. Adhesion</subject><subject>B. Stress transfer</subject><subject>Bonding</subject><subject>C. Finite element analysis (FEA)</subject><subject>Composites</subject><subject>Emission</subject><subject>Exact sciences and technology</subject><subject>Fatigue cracks</subject><subject>Forms of application and semi-finished materials</subject><subject>Laminates</subject><subject>Mathematical analysis</subject><subject>Mathematical models</subject><subject>Physicochemistry of polymers</subject><subject>Polymer industry, paints, wood</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>2013</creationdate><recordtype>article</recordtype><recordid>eNqNkc1u1DAUhSNEJUrLO5gFEpsE_yROsqxG_EmV2MDacq6vOx4SO9gOaN6Fh62jqSqWeOO7-O459jlV9ZbRhlEmP5waCMsaksuYpoZTxhs6NJSNL6prNvRjzagcX5ZZdGM9CDm8ql6ndKKUtp3g19XfO6_nc3agZ2JDXLZZZxc8CZbkI5KUI6ZEnM_oi8eZWA05xB0lEDX8JLhoX1b8A7ExLATQ51i0jmHGRLQ3JOKqXURD_rh8JFPwpszPjyarznAsBqRARdHm3XODvBXj2-rK6jnhm6f7pvrx6eP3w5f6_tvnr4e7-xpa1udaojFcC-QdtPuRTPBuAguT1BPFnoGhIKzh2La9LYHIVlCYrJacSms6cVO9v-iuMfzaMGW1uAQ4z9pj2JJiA--6thXdUNDxgkIMKUW0ao1u0fGsGFV7I-qk_mlE7Y0oOqjSSNl992SjU8nbRu3BpWcBLvtB9nTnDhcOy59_O4wqgUMPaEqOkJUJ7j_cHgE7y60S</recordid><startdate>20130201</startdate><enddate>20130201</enddate><creator>Albedah, A.</creator><creator>Benyahia, F.</creator><creator>Dinar, H.</creator><creator>Bachir Bouiadjra, B.</creator><general>Elsevier Ltd</general><general>Elsevier</general><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7SR</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>JG9</scope><scope>KR7</scope></search><sort><creationdate>20130201</creationdate><title>Analytical formulation of the stress intensity factor for crack emanating from central holes and repaired with bonded composite patch in aircraft structures</title><author>Albedah, A. ; Benyahia, F. ; Dinar, H. ; Bachir Bouiadjra, B.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c417t-6edd2a3e25c4444461325bcfcb6ab0e71cd0c3fd2e447f1066430cbfa6206fd53</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2013</creationdate><topic>A. Layered structures</topic><topic>Aircraft components</topic><topic>Aircraft structures</topic><topic>Applied sciences</topic><topic>B. Adhesion</topic><topic>B. Stress transfer</topic><topic>Bonding</topic><topic>C. Finite element analysis (FEA)</topic><topic>Composites</topic><topic>Emission</topic><topic>Exact sciences and technology</topic><topic>Fatigue cracks</topic><topic>Forms of application and semi-finished materials</topic><topic>Laminates</topic><topic>Mathematical analysis</topic><topic>Mathematical models</topic><topic>Physicochemistry of polymers</topic><topic>Polymer industry, paints, wood</topic><topic>Stress intensity factor</topic><topic>Technology of polymers</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Albedah, A.</creatorcontrib><creatorcontrib>Benyahia, F.</creatorcontrib><creatorcontrib>Dinar, H.</creatorcontrib><creatorcontrib>Bachir Bouiadjra, B.</creatorcontrib><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Engineered Materials Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Materials Research Database</collection><collection>Civil Engineering Abstracts</collection><jtitle>Composites. 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This study was performed in order to establish an analytical model for the stress intensity factor for repaired crack emanating from central holes. The model was developed by modifying that of Kujawski initially developed for cracks emanating from notch without repair. The obtained results were compared with those calculated with the finite element method and the model of Jones et al. It was found that our model gives a good approximation of the stress intensity factor for repaired crack emanating from central elliptical and circular holes if the results of the finite element analysis are taken as references.</abstract><cop>Kidlington</cop><pub>Elsevier Ltd</pub><doi>10.1016/j.compositesb.2012.08.019</doi><tpages>6</tpages></addata></record> |
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| source | Elsevier ScienceDirect Journals |
| subjects | A. Layered structures Aircraft components Aircraft structures Applied sciences B. Adhesion B. Stress transfer Bonding C. Finite element analysis (FEA) Composites Emission Exact sciences and technology Fatigue cracks Forms of application and semi-finished materials Laminates Mathematical analysis Mathematical models Physicochemistry of polymers Polymer industry, paints, wood Stress intensity factor Technology of polymers |
| title | Analytical formulation of the stress intensity factor for crack emanating from central holes and repaired with bonded composite patch in aircraft structures |
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