Accession Number : ADA188072
Title : Impact Damage Tolerance of a Carbon Fibre Composite Laminate.
Descriptive Note : Technical rept.,
Corporate Author : ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
Personal Author(s) : Dorey, G ; Sigety, P ; Stellbrink, K ; Hart, W G
PDF Url : ADA188072
Report Date : May 1984
Pagination or Media Count : 47
Abstract : An investigation was carried out, under the auspices of GARTEUR, at four European aerospace research establishments as the first phase of a collaborative research programme on impact damage tolerance of composite materials. Laminates, from a common batch of material having a 0 90 -+ 45 0 s lay up, were impacted by dropweight and residual strengths were measured under fully reversed loading for specimens containing barely visible impact damage. The impact damage significantly reduced the static compressive strength but subsequent fatigue loading produced little further reduction in strength and the fatigue strength at 10 to the 6th power cycles was similar to that for non impacted specimens. All four establishments produced similar results and in Phase 2 they will study in more detail a wider range of materials and test parameters. Keywords: Carbon fibre, Composite material, Impact, Fatigue, Residual strength, Barely visible impact damage.
Descriptors : *FIBER REINFORCED COMPOSITES, *LAMINATES, *CARBON REINFORCED COMPOSITES, *IMPACT STRENGTH, *TOUGHNESS, BATCH PROCESSING, CARBON FIBERS, COMPRESSIVE PROPERTIES, DAMAGE, FATIGUE(MECHANICS), IMPACT, LOADS(FORCES), RESIDUALS, REVERSIBLE, STRENGTH(MECHANICS), TOLERANCES(MECHANICS), VISIBILITY, DROP TESTS, IMPACT TESTS, DAMAGE ASSESSMENT, FATIGUE TESTS(MECHANICS), TENSILE STRENGTH, STATIC TESTS, ULTRASONIC TESTS, GREAT BRITAIN
Subject Categories : Laminates and Composite Materials
Distribution Statement : APPROVED FOR PUBLIC RELEASE