Print Email Facebook Twitter The effect of sheet thickness and laminating on the fatigue resistance of the aluminium alloyd AL-7010T73651 Title The effect of sheet thickness and laminating on the fatigue resistance of the aluminium alloyd AL-7010T73651 Author van der Hoeven, W. Schra, L. Institution National Aerospace Laboratory NLR Date 1981-03-31 Abstract The influence of sheet thickness (2 mm and 10 mm) and the influence of laminating (5x2 ram) on the fatigue crack growth properties of the aluminium alloy AL 7010-T 73651 were investigated. Both constant amplitude loading and flight simulation loading were applied. All 2 mm and 10 mm thick sheets were machined from a 150 mm thick plate, i.e. there were no differences in production history between those sheets. Only for flight simulation testing a pronounced thickness effect was observed with the thinner sheet (2 mm) showing a superior behavious. It could be concluded that this thickness effect is most probably the result of differences in the state of stress and is not caused by differences in production history. For flight simulation loading the fatigue resistance of the laminates was found comparable to that of the monolitic 10 mm thick sheets. For constant amplitude loading the fatigue resistance of the laminates was even lower than that of the monolitic 10 mm sheets. Subject High strength alloysAluminium alloysAdhesive bondingLaminatesFatigue testsGust loadsFlight simulationThicknessFatigue strengthCrack propagationFractography To reference this document use: http://resolver.tudelft.nl/uuid:e3235ee1-8fb4-4406-9565-3006ee4894d0 Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 81056 U Part of collection Aerospace Engineering Reports Document type report Rights (c)1981 National Aerospace Laboratory NLR Files PDF NLR_TR_81056_U.pdf 20.05 MB Close viewer /islandora/object/uuid:e3235ee1-8fb4-4406-9565-3006ee4894d0/datastream/OBJ/view