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| 02855nam 2200433zi 4500 |
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| 001 | 9.936156 |
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| 003 | CaOODSP |
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| 005 | 20241007095055 |
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| 006 | m o d f |
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| 007 | cr |n||||||||| |
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| 008 | 240328e198812uubccad obt f000 0 eng d |
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| 040 | |aCaOODSP|beng|erda|cCaOODSP |
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| 043 | |an-cn--- |
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| 086 | 1 |aDR52-11/4-1988E-PDF |
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| 100 | 1 |aRussell, Alan J., |eauthor. |
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| 245 | 12|aA damage tolerance assessment of bonded repairs to CF-18 composite components : |bpart I: adhesive properties / |cA.J. Russell. |
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| 264 | 1|aVictoria, B.C. : |bDefence Research Establishment Pacific = Centre de recherches pour la défense pacifique : |bResearch and Development Branch, Department of National Defence Canada, |cDecember 1988 |
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| 300 | |a1 online resource (27, [2] pages) : |billustrations, charts |
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| 336 | |atext|btxt|2rdacontent |
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| 337 | |acomputer|bc|2rdamedia |
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| 338 | |aonline resource|bcr|2rdacarrier |
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| 490 | 1 |aTechnical memorandum ; |v88-25 |
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| 500 | |aTitle from cover page. |
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| 500 | |aDigitized edition from print [produced by Defence Research and Development Canada]. |
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| 504 | |aIncludes bibliographical references (page 27). |
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| 520 | 3 |a"The damage tolerance properties of three epoxy adhesives used in the manufacture and repair of the composite structure on the CF-18 aircraft are assessed. The resistance to both static fracture and fatigue crack growth are evaluated. Experimental variables include the mode of fracture (tension and shear), the fatigue load ratio, the test temperature and the method of bonding. Both the static and fatigue tests were found to rank the adhesives in the same order, viz. FM-300K superior to FM-300 superior to EA-9321. The fatigue testing revealed a tendency for delamination type failures to occur at low temperature, a situation likely to lead to non-conservative joint designs. The fatigue crack growth rate data are explained in terms of the failure mechanisms observed. The implication of these findings to the selection of repair adhesives for composite aircraft structure is discussed."--abstract. |
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| 650 | 0|aGraphite composites|xTesting. |
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| 650 | 0|aAdhesive joints|xTesting. |
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| 650 | 0|aAirframes|xFatigue. |
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| 650 | 6|aComposites de graphite|xTests. |
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| 650 | 6|aAssemblages collés|xTests. |
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| 650 | 6|aCellules (Aéronautique)|xFatigue. |
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| 655 | 7|aTechnical reports|2lcgft |
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| 655 | 7|aRapports techniques|2rvmgf |
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| 710 | 2 |aDefence Research Establishment Pacific, |eissuing body. |
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| 710 | 1 |aCanada. |bDepartment of National Defence. |cResearch and Development Branch,|eissuing body. |
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| 830 | #0|aTechnical memorandum (Defence Research Establishment Pacific)|v88-25.|w(CaOODSP)9.936067 |
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| 856 | 40|qPDF|s924 KB|uhttps://publications.gc.ca/collections/collection_2024/rddc-drdc/DR52-11-4-1988-eng.pdf |
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