Aluminum-copper-magnesium-manganese alloy useful for aircraft ap

Metal treatment – Process of modifying or maintaining internal physical... – Heating or cooling of solid metal

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148700, 148417, 148439, C22F 104

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058977201

ABSTRACT:
A product comprising an aluminum base alloy including about 3.8 wt. % copper, about 1.2 wt. % magnesium, about 0.3 to 0.6 wt. % manganese, not more than about 0.15 wt. % silicon, not more than about 0.12 wt. % iron, not more than about 0.1 wt. % titanium, the remainder substantially aluminum, incidental elements and impurities, the product having at least 5% improvement over 2024 alloy in fracture toughness, fatigue crack growth rate, corrosion resistance, and formability properties.

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patent: 5273594 (1993-12-01), Cassada
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Technical Report AFML-TR-247, vol. II Sep., 1974.
Thompson et al., "Special Processing of Al-Cu-Mg Alloys", Abstract 651872, MA No. 79-560035 (1979).
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Reynolds Report AD-770-350 "Program to Improve the Facture Toughness and Fatigue Resistance of Aluminum Sheet and Plate for Aircraft Applications", Sep., 1973, pp. 1-105.
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Titchener et al., "The Effect of Thermomechanical Treatment on the Fatigue Behaviour of an Al-Mg-Si-Mn Alloy", Department of Chemical and Materails Engineering, University of Auckland, Aug. 1973, pp. 432-436.
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