Biaxial testing of cruciform specimens representing characteristics of a metallic airplane fuselage section
•Biaxial tests of cruciform specimen representing an aircraft fuselage section.•Experimental study of fatigue cracks in aluminum alloys with ΔK up to 130 MPa√m.•Calculation of stress intensity factors based on digital image correlation (DIC).•Determination of ΔKeff with DIC results. Based on biaxial...
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| Veröffentlicht in: | International journal of fatigue 2018-03, Vol.108, p.116-126 |
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| container_title | International journal of fatigue |
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| creator | Breitbarth, Eric Besel, Michael Reh, Stefan |
| description | •Biaxial tests of cruciform specimen representing an aircraft fuselage section.•Experimental study of fatigue cracks in aluminum alloys with ΔK up to 130 MPa√m.•Calculation of stress intensity factors based on digital image correlation (DIC).•Determination of ΔKeff with DIC results.
Based on biaxial tests with cruciform specimens, the scenario of fatigue cracks in the upper fuselage section between the wings and the tail unit of a commercial single aisle aircraft has been studied. Two different types of specimen were designed, namely for the scenario of a circumferential crack across a broken stringer and for a longitudinal crack parallel to the stringers. With crack length up to 2a ≈ 610 mm, maximum mode I stress intensity factors of 160 MPa√m were obtained for the commercial aluminum alloys AA2024-T351 and AA5028-H116. All experiments were supported by digital image correlation to obtain the actual deformation fields of the specimens. Based on these data stress intensity factors and J integrals were computed with a line integral procedure. Furthermore, plastic zone and crack closure effects were studied. |
| doi_str_mv | 10.1016/j.ijfatigue.2017.12.005 |
| format | Article |
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Based on biaxial tests with cruciform specimens, the scenario of fatigue cracks in the upper fuselage section between the wings and the tail unit of a commercial single aisle aircraft has been studied. Two different types of specimen were designed, namely for the scenario of a circumferential crack across a broken stringer and for a longitudinal crack parallel to the stringers. With crack length up to 2a ≈ 610 mm, maximum mode I stress intensity factors of 160 MPa√m were obtained for the commercial aluminum alloys AA2024-T351 and AA5028-H116. All experiments were supported by digital image correlation to obtain the actual deformation fields of the specimens. Based on these data stress intensity factors and J integrals were computed with a line integral procedure. Furthermore, plastic zone and crack closure effects were studied.</description><identifier>ISSN: 0142-1123</identifier><identifier>EISSN: 1879-3452</identifier><identifier>DOI: 10.1016/j.ijfatigue.2017.12.005</identifier><language>eng</language><publisher>Kidlington: Elsevier Ltd</publisher><subject>Aging aircraft ; Airframes ; Aluminum ; Aluminum base alloys ; Biaxial testing ; Biaxial tests ; Commercial aircraft ; Crack closure ; Crack propagation ; Cracks ; Cruciform tests ; Deformation ; Digital image correlation ; Digital imaging ; Fatigue crack ; Fatigue cracks ; Fatigue failure ; Fatigue tests ; Fuselages ; Integrals ; Materials fatigue ; Plastic zone ; Stress intensity factors ; Stringers ; Wings (aircraft)</subject><ispartof>International journal of fatigue, 2018-03, Vol.108, p.116-126</ispartof><rights>2017 Elsevier Ltd</rights><rights>Copyright Elsevier BV Mar 2018</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c343t-f1c83e0572f7bedd74f1f7701d2d62b73f3ee614e5fb459fd336ae01ce54d2f53</citedby><cites>FETCH-LOGICAL-c343t-f1c83e0572f7bedd74f1f7701d2d62b73f3ee614e5fb459fd336ae01ce54d2f53</cites><orcidid>0000-0002-3479-9143</orcidid></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://dx.doi.org/10.1016/j.ijfatigue.2017.12.005$$EHTML$$P50$$Gelsevier$$H</linktohtml><link.rule.ids>314,776,780,3536,27903,27904,45974</link.rule.ids></links><search><creatorcontrib>Breitbarth, Eric</creatorcontrib><creatorcontrib>Besel, Michael</creatorcontrib><creatorcontrib>Reh, Stefan</creatorcontrib><title>Biaxial testing of cruciform specimens representing characteristics of a metallic airplane fuselage section</title><title>International journal of fatigue</title><description>•Biaxial tests of cruciform specimen representing an aircraft fuselage section.•Experimental study of fatigue cracks in aluminum alloys with ΔK up to 130 MPa√m.•Calculation of stress intensity factors based on digital image correlation (DIC).•Determination of ΔKeff with DIC results.
Based on biaxial tests with cruciform specimens, the scenario of fatigue cracks in the upper fuselage section between the wings and the tail unit of a commercial single aisle aircraft has been studied. Two different types of specimen were designed, namely for the scenario of a circumferential crack across a broken stringer and for a longitudinal crack parallel to the stringers. With crack length up to 2a ≈ 610 mm, maximum mode I stress intensity factors of 160 MPa√m were obtained for the commercial aluminum alloys AA2024-T351 and AA5028-H116. All experiments were supported by digital image correlation to obtain the actual deformation fields of the specimens. Based on these data stress intensity factors and J integrals were computed with a line integral procedure. Furthermore, plastic zone and crack closure effects were studied.</description><subject>Aging aircraft</subject><subject>Airframes</subject><subject>Aluminum</subject><subject>Aluminum base alloys</subject><subject>Biaxial testing</subject><subject>Biaxial tests</subject><subject>Commercial aircraft</subject><subject>Crack closure</subject><subject>Crack propagation</subject><subject>Cracks</subject><subject>Cruciform tests</subject><subject>Deformation</subject><subject>Digital image correlation</subject><subject>Digital imaging</subject><subject>Fatigue crack</subject><subject>Fatigue cracks</subject><subject>Fatigue failure</subject><subject>Fatigue tests</subject><subject>Fuselages</subject><subject>Integrals</subject><subject>Materials fatigue</subject><subject>Plastic zone</subject><subject>Stress intensity factors</subject><subject>Stringers</subject><subject>Wings (aircraft)</subject><issn>0142-1123</issn><issn>1879-3452</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2018</creationdate><recordtype>article</recordtype><recordid>eNqFkMtOwzAQRS0EEqXwDVhinTB-xc2yVLykSmxgbbnOuDikSbATBH9PShFbVrO5547uIeSSQc6AFdd1Hmpvh7AdMefAdM54DqCOyIwtdJkJqfgxmQGTPGOMi1NyllINACVoNSNvN8F-BtvQAdMQ2i3tPHVxdMF3cUdTjy7ssE00Yh8xYfuTca82WjdgDBPj0p6xdIeDbZrgqA2xb2yL1I8JG7tFmtANoWvPyYm3TcKL3zsnL3e3z6uHbP10_7harjMnpBgyz9xCICjNvd5gVWnpmdcaWMWrgm-08AKxYBKV30hV-kqIwiIwh0pW3CsxJ1eH3j527-O0y9TdGNvppeGgoACpF-WU0oeUi11KEb3pY9jZ-GUYmL1ZU5s_s2Zv1jBuJrMTuTyQOI34CBhNcgFbh1WI01JTdeHfjm-kdYj7</recordid><startdate>201803</startdate><enddate>201803</enddate><creator>Breitbarth, Eric</creator><creator>Besel, Michael</creator><creator>Reh, Stefan</creator><general>Elsevier Ltd</general><general>Elsevier BV</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7SR</scope><scope>8BQ</scope><scope>8FD</scope><scope>JG9</scope><orcidid>https://orcid.org/0000-0002-3479-9143</orcidid></search><sort><creationdate>201803</creationdate><title>Biaxial testing of cruciform specimens representing characteristics of a metallic airplane fuselage section</title><author>Breitbarth, Eric ; Besel, Michael ; Reh, Stefan</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c343t-f1c83e0572f7bedd74f1f7701d2d62b73f3ee614e5fb459fd336ae01ce54d2f53</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2018</creationdate><topic>Aging aircraft</topic><topic>Airframes</topic><topic>Aluminum</topic><topic>Aluminum base alloys</topic><topic>Biaxial testing</topic><topic>Biaxial tests</topic><topic>Commercial aircraft</topic><topic>Crack closure</topic><topic>Crack propagation</topic><topic>Cracks</topic><topic>Cruciform tests</topic><topic>Deformation</topic><topic>Digital image correlation</topic><topic>Digital imaging</topic><topic>Fatigue crack</topic><topic>Fatigue cracks</topic><topic>Fatigue failure</topic><topic>Fatigue tests</topic><topic>Fuselages</topic><topic>Integrals</topic><topic>Materials fatigue</topic><topic>Plastic zone</topic><topic>Stress intensity factors</topic><topic>Stringers</topic><topic>Wings (aircraft)</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Breitbarth, Eric</creatorcontrib><creatorcontrib>Besel, Michael</creatorcontrib><creatorcontrib>Reh, Stefan</creatorcontrib><collection>CrossRef</collection><collection>Engineered Materials Abstracts</collection><collection>METADEX</collection><collection>Technology Research Database</collection><collection>Materials Research Database</collection><jtitle>International journal of fatigue</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Breitbarth, Eric</au><au>Besel, Michael</au><au>Reh, Stefan</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Biaxial testing of cruciform specimens representing characteristics of a metallic airplane fuselage section</atitle><jtitle>International journal of fatigue</jtitle><date>2018-03</date><risdate>2018</risdate><volume>108</volume><spage>116</spage><epage>126</epage><pages>116-126</pages><issn>0142-1123</issn><eissn>1879-3452</eissn><abstract>•Biaxial tests of cruciform specimen representing an aircraft fuselage section.•Experimental study of fatigue cracks in aluminum alloys with ΔK up to 130 MPa√m.•Calculation of stress intensity factors based on digital image correlation (DIC).•Determination of ΔKeff with DIC results.
Based on biaxial tests with cruciform specimens, the scenario of fatigue cracks in the upper fuselage section between the wings and the tail unit of a commercial single aisle aircraft has been studied. Two different types of specimen were designed, namely for the scenario of a circumferential crack across a broken stringer and for a longitudinal crack parallel to the stringers. With crack length up to 2a ≈ 610 mm, maximum mode I stress intensity factors of 160 MPa√m were obtained for the commercial aluminum alloys AA2024-T351 and AA5028-H116. All experiments were supported by digital image correlation to obtain the actual deformation fields of the specimens. Based on these data stress intensity factors and J integrals were computed with a line integral procedure. Furthermore, plastic zone and crack closure effects were studied.</abstract><cop>Kidlington</cop><pub>Elsevier Ltd</pub><doi>10.1016/j.ijfatigue.2017.12.005</doi><tpages>11</tpages><orcidid>https://orcid.org/0000-0002-3479-9143</orcidid></addata></record> |
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| ispartof | International journal of fatigue, 2018-03, Vol.108, p.116-126 |
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| language | eng |
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| source | Elsevier ScienceDirect Journals |
| subjects | Aging aircraft Airframes Aluminum Aluminum base alloys Biaxial testing Biaxial tests Commercial aircraft Crack closure Crack propagation Cracks Cruciform tests Deformation Digital image correlation Digital imaging Fatigue crack Fatigue cracks Fatigue failure Fatigue tests Fuselages Integrals Materials fatigue Plastic zone Stress intensity factors Stringers Wings (aircraft) |
| title | Biaxial testing of cruciform specimens representing characteristics of a metallic airplane fuselage section |
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