FATIGUE CRACK GROWTH THROUGH ARALL-4 AT AMBIENT TEMPERATURE
Fatigue cracks were grown in the 5 layer aluminum alloy‐Aramid fiber laminate composite ARALL‐4 over the range of cyclic stress intensity factors (ΔK) from 3.5 to 91 MPa✓m. Near the threshold, crack growth rate was about the same as for unreinforced aluminum alloys, but at high ΔK, crack growth rate...
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| Veröffentlicht in: | Fatigue & fracture of engineering materials & structures 1991-10, Vol.14 (10), p.939-951 |
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| container_title | Fatigue & fracture of engineering materials & structures |
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| creator | Davidson1, D. L. Austin2, L. K. |
| description | Fatigue cracks were grown in the 5 layer aluminum alloy‐Aramid fiber laminate composite ARALL‐4 over the range of cyclic stress intensity factors (ΔK) from 3.5 to 91 MPa✓m. Near the threshold, crack growth rate was about the same as for unreinforced aluminum alloys, but at high ΔK, crack growth rates were significantly lower. Crack closure was measured over this range of growth rates and found to be different than for unreinforced aluminum alloys. The magnitude of closure was also dependent on crack length. Cracks opened progressively towards the tip with increasing load in much the same way as for unreinforced aluminum alloys. Removal of the aluminum outer layer and some of the epoxy revealed that fibers were intact close to the crack tip, but heavily damaged further away. By adjusting the fatigue crack growth curve of an unreinforced aluminum alloy for the closure exhibited by the composite, it was possible to approximate the crack growth rate for the composite over the lower to mid range of ΔK, but at higher values of ΔK, this model seriously overestimated measured crack growth rates. Therefore, fiber bridging affects both closure and maximum stress intensity factor at the crack tip. Standard fracture mechanics cannot be applied to describe these effects. |
| doi_str_mv | 10.1111/j.1460-2695.1991.tb00004.x |
| format | Article |
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L. ; Austin2, L. K.</creator><creatorcontrib>Davidson1, D. L. ; Austin2, L. K.</creatorcontrib><description>Fatigue cracks were grown in the 5 layer aluminum alloy‐Aramid fiber laminate composite ARALL‐4 over the range of cyclic stress intensity factors (ΔK) from 3.5 to 91 MPa✓m. Near the threshold, crack growth rate was about the same as for unreinforced aluminum alloys, but at high ΔK, crack growth rates were significantly lower. Crack closure was measured over this range of growth rates and found to be different than for unreinforced aluminum alloys. The magnitude of closure was also dependent on crack length. Cracks opened progressively towards the tip with increasing load in much the same way as for unreinforced aluminum alloys. Removal of the aluminum outer layer and some of the epoxy revealed that fibers were intact close to the crack tip, but heavily damaged further away. By adjusting the fatigue crack growth curve of an unreinforced aluminum alloy for the closure exhibited by the composite, it was possible to approximate the crack growth rate for the composite over the lower to mid range of ΔK, but at higher values of ΔK, this model seriously overestimated measured crack growth rates. Therefore, fiber bridging affects both closure and maximum stress intensity factor at the crack tip. Standard fracture mechanics cannot be applied to describe these effects.</description><identifier>ISSN: 8756-758X</identifier><identifier>EISSN: 1460-2695</identifier><identifier>DOI: 10.1111/j.1460-2695.1991.tb00004.x</identifier><identifier>CODEN: FFESEY</identifier><language>eng</language><publisher>Oxford, UK: Blackwell Publishing Ltd</publisher><subject>Applied sciences ; crack propagation ; Exact sciences and technology ; Fatigue ; Mechanical properties and methods of testing. Rheology. Fracture mechanics. Tribology ; Metals. 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L.</creatorcontrib><creatorcontrib>Austin2, L. K.</creatorcontrib><title>FATIGUE CRACK GROWTH THROUGH ARALL-4 AT AMBIENT TEMPERATURE</title><title>Fatigue & fracture of engineering materials & structures</title><description>Fatigue cracks were grown in the 5 layer aluminum alloy‐Aramid fiber laminate composite ARALL‐4 over the range of cyclic stress intensity factors (ΔK) from 3.5 to 91 MPa✓m. Near the threshold, crack growth rate was about the same as for unreinforced aluminum alloys, but at high ΔK, crack growth rates were significantly lower. Crack closure was measured over this range of growth rates and found to be different than for unreinforced aluminum alloys. The magnitude of closure was also dependent on crack length. Cracks opened progressively towards the tip with increasing load in much the same way as for unreinforced aluminum alloys. Removal of the aluminum outer layer and some of the epoxy revealed that fibers were intact close to the crack tip, but heavily damaged further away. By adjusting the fatigue crack growth curve of an unreinforced aluminum alloy for the closure exhibited by the composite, it was possible to approximate the crack growth rate for the composite over the lower to mid range of ΔK, but at higher values of ΔK, this model seriously overestimated measured crack growth rates. Therefore, fiber bridging affects both closure and maximum stress intensity factor at the crack tip. Standard fracture mechanics cannot be applied to describe these effects.</description><subject>Applied sciences</subject><subject>crack propagation</subject><subject>Exact sciences and technology</subject><subject>Fatigue</subject><subject>Mechanical properties and methods of testing. Rheology. Fracture mechanics. Tribology</subject><subject>Metals. Metallurgy</subject><subject>stress intensity factor</subject><issn>8756-758X</issn><issn>1460-2695</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>1991</creationdate><recordtype>article</recordtype><recordid>eNqVkF1r2zAUhkVZoVnb_2DG2K7sSpaPPjYYuMaxQ9OmGIfsTiiKDM6cpLNSlv77yiTkctBzows9el-dB6EvBEfEz906IgnDYcwkRERKEu2X2E8SHS7Q6Hz1CY0EBxZyEL-v0Gfn1hgTllA6Qj_HaT0p5nmQVWn2EBTVbFGXQV1Ws3lRBmmVTqdhEqR1kD7eT_KnOqjzx-e8Sut5ld-gy0Z3zt6ezms0H-d1VobTWTHJ0mlogMQy5IYRzDhZEb5M9JIyAasYhMAglqyxwKxk0DADjf8Tj6VpMOfUCMqllgCSXqPvx9yXfvf31bq92rTO2K7TW7t7dYr7PSkAFZ789l8yhpgIJhIP_jiCpt8519tGvfTtRvdvimA1mFVrNehTgz41mFUns-rgH389tWhndNf0emtad04AGksM2GO_jti_trNvHyhQ43Eu6bB3eAxo3d4ezgG6_6MYpxzU4qlQ9xyKTJSZr30HriOT2Q</recordid><startdate>199110</startdate><enddate>199110</enddate><creator>Davidson1, D. L.</creator><creator>Austin2, L. K.</creator><general>Blackwell Publishing Ltd</general><general>Blackwell Science</general><scope>BSCLL</scope><scope>IQODW</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>7QF</scope><scope>7U5</scope><scope>8BQ</scope><scope>8FD</scope><scope>H8D</scope><scope>JG9</scope><scope>L7M</scope><scope>7TC</scope></search><sort><creationdate>199110</creationdate><title>FATIGUE CRACK GROWTH THROUGH ARALL-4 AT AMBIENT TEMPERATURE</title><author>Davidson1, D. L. ; Austin2, L. K.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c5129-7c610671d17b4ab3685d2588058b6fe56e965f6c5f164729cf0773c8379a95593</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>1991</creationdate><topic>Applied sciences</topic><topic>crack propagation</topic><topic>Exact sciences and technology</topic><topic>Fatigue</topic><topic>Mechanical properties and methods of testing. Rheology. Fracture mechanics. Tribology</topic><topic>Metals. Metallurgy</topic><topic>stress intensity factor</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Davidson1, D. L.</creatorcontrib><creatorcontrib>Austin2, L. K.</creatorcontrib><collection>Istex</collection><collection>Pascal-Francis</collection><collection>CrossRef</collection><collection>Aluminium Industry Abstracts</collection><collection>Solid State and Superconductivity Abstracts</collection><collection>METADEX</collection><collection>Technology Research Database</collection><collection>Aerospace Database</collection><collection>Materials Research Database</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Mechanical Engineering Abstracts</collection><jtitle>Fatigue & fracture of engineering materials & structures</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Davidson1, D. L.</au><au>Austin2, L. K.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>FATIGUE CRACK GROWTH THROUGH ARALL-4 AT AMBIENT TEMPERATURE</atitle><jtitle>Fatigue & fracture of engineering materials & structures</jtitle><date>1991-10</date><risdate>1991</risdate><volume>14</volume><issue>10</issue><spage>939</spage><epage>951</epage><pages>939-951</pages><issn>8756-758X</issn><eissn>1460-2695</eissn><coden>FFESEY</coden><abstract>Fatigue cracks were grown in the 5 layer aluminum alloy‐Aramid fiber laminate composite ARALL‐4 over the range of cyclic stress intensity factors (ΔK) from 3.5 to 91 MPa✓m. Near the threshold, crack growth rate was about the same as for unreinforced aluminum alloys, but at high ΔK, crack growth rates were significantly lower. Crack closure was measured over this range of growth rates and found to be different than for unreinforced aluminum alloys. The magnitude of closure was also dependent on crack length. Cracks opened progressively towards the tip with increasing load in much the same way as for unreinforced aluminum alloys. Removal of the aluminum outer layer and some of the epoxy revealed that fibers were intact close to the crack tip, but heavily damaged further away. By adjusting the fatigue crack growth curve of an unreinforced aluminum alloy for the closure exhibited by the composite, it was possible to approximate the crack growth rate for the composite over the lower to mid range of ΔK, but at higher values of ΔK, this model seriously overestimated measured crack growth rates. Therefore, fiber bridging affects both closure and maximum stress intensity factor at the crack tip. Standard fracture mechanics cannot be applied to describe these effects.</abstract><cop>Oxford, UK</cop><pub>Blackwell Publishing Ltd</pub><doi>10.1111/j.1460-2695.1991.tb00004.x</doi><tpages>13</tpages></addata></record> |
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| ispartof | Fatigue & fracture of engineering materials & structures, 1991-10, Vol.14 (10), p.939-951 |
| issn | 8756-758X 1460-2695 |
| language | eng |
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| source | Wiley Online Library Journals Frontfile Complete |
| subjects | Applied sciences crack propagation Exact sciences and technology Fatigue Mechanical properties and methods of testing. Rheology. Fracture mechanics. Tribology Metals. Metallurgy stress intensity factor |
| title | FATIGUE CRACK GROWTH THROUGH ARALL-4 AT AMBIENT TEMPERATURE |
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