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AssigneeAluminum Company of America
InventorsEdward L. Colvin, Jocelyn I. Petit, Robert W. Westerlund, Paul E. Magnusen
Estimating the term…
A method of producing a sheet product and improved products having improved levels of toughness and fatigue crack growth resistance at good strength levels. The method comprises providing an aluminum base alloy containing 4 to 4.5% Cu, 1.2 to 1.5% Mg, 0.4 to 0.6% Mn, 0.12% max. Fe, 0.1% max. Si, the remainder aluminum, incidental elements and impurities and hot rolling the alloy, heating the alloy to above 910.degree. F. and additionally hot rolling it in a range of about 600.degree. to 900.degree. F., solution heat treating, preferably for a time of less than about 15 minutes at a solution heat treating temperature, and rapidly cooling and naturally aging. The invention products have very good combinations of strength together with high fracture toughness or low fatigue crack growth rate, or both, making them well suited for aerospace applications such as fuselage skin. The products preferably include a corrosion protecting cladding of aluminum or aluminum alloy.
A method of producing an aluminum product comprising:
A method of producing an aluminum sheet or plate product comprising:
A method of producing an aluminum sheet or plate product comprising:
A method of producing a clad aluminum product comprising:
A method of producing a clad aluminum sheet or plate product comprising:
A method of producing a clad aluminum sheet or plate product comprising:
A method of producing a clad aluminum product having good strength along with good fracture toughness or good resistance to fatigue crack growth, or both, said method comprising:
A method of producing a clad aluminum sheet or plate product comprising:
A method of producing an aluminum sheet or plate product comprising:
A method of producing a clad aluminum product comprising:
A method of producing a clad aluminum sheet product comprising:
A method of producing a clad aluminum product having good strength along with good fracture toughness or good resistance to fatigue crack growth, or both, said method comprising:
A method of producing a clad aluminum product having good strength along with good fracture toughness or good resistance to fatigue crack growth, or both, said method comprising:
In a method wherein an aluminum alloy stock is shaped into an airplane member, the improvement wherein said stock is provided by a method comprising:
In a method wherein an aluminum alloy stock is shaped into an airplane member, the improvement wherein said stock is provided by a method comprising:
In a method wherein an aluminum alloy sheet is shaped into an airplane member, the improvement wherein said sheet is provided by a method comprising:
In a method wherein an aluminum alloy material is shaped into a vehicular panel, the improvement wherein said material is provided by a method comprising:
In a method wherein an aluminum alloy material is shaped into a vehicular panel, the improvement wherein said material is provided by a method comprising:
A product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said product having at least 5% improvement over 2024 alloy in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 15ksi.sqroot.in or more, or in both said (a) and (b) properties.
An aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.3 to 0.8% manganese, and containing not more than about 0.15% iron, not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, said product having a long transverse yield strength of 38 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 15 ksi.sqroot.in or more, or in both said (a) and (b) properties.
An aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy product having one or more of the following properties:
An aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, and containing not more than 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy product having a long transverse yield strength of 38 ksi or more together with one or more of the following properties:
An aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.3 to 0.9 manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, said sheet having a long transverse yield strength of 39 ksi or more and a minimum T-L fracture toughness K.sub.c of at least 140 ksi.sqroot.in or more and a fatigue crack growth rate not greater than 5% above one or more of the levels shown in FIG. 8 or 9.
An aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.4 to 0.78% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, said sheet having a long transverse yield strength of 38 ksi or more and a minimum T-L fracture toughness K.sub.app of 80 ksi.sqroot.in. or more and a fatigue crack growth rate not greater than 5% above one or more of the levels shown in FIG. 8 or 9.
An aluminum alloy sheet or plate product comprising a first aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said first alloy on one or more faces thereof, said sheet having a minimum long transverse yield strength of 38 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 15 ksi.sqroot.in or more, or in both said properties.
An aluminum alloy sheet or plate product comprising a first aluminum base alloy consisting essentially of, by weight, about 4 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.3 to 0.8% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said first alloy on one or more faces thereof, said sheet having a minimum long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of ksi.sqroot.in or more, or in both said properties.
An aluminum alloy sheet or plate product comprising a first aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said first alloy on one or more faces thereof, said sheet having a long transverse yield strength of 39 ksi or more together with one or more of the following properties:
An aluminum alloy sheet or plate product comprising a first aluminum base alloy consisting essentially of, by weight, about 4 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.4 to 0.7% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer on one or more faces thereof, said sheet having a long transverse yield strength of 40 ksi or more and a minimum T-L fracture toughness K.sub.c of 140 ksi.sqroot.in or more and a fatigue crack growth rate not greater than 5% above one or more of the levels shown in FIG. 8 or 9.
An aluminum alloy sheet product having a core of an aluminum base alloy consisting essentially of, by weight, about 4 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.4 to 0.7% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer on one or more faces thereof, said sheet having a long transverse yield strength of 39 ksi or more and a minimum T-L fracture toughness K.sub.app of 80 ksi.sqroot.in. or more and a fatigue crack growth rate not greater than 5% above one or more of the levels shown in FIG. 8 or 9.
An aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy having a long transverse yield strength of 39 ksi or more and exhibiting an average fatigue crack growth rate of not over 1.4.times.10.sup.-4 inch per cycle for growing a crack from about 1.7 inch to about 1 inch at a frequency of about 25 hertz and a stress ratio R of 0.1 and a substantially constant .DELTA.K of about 30 ksi.sqroot.in in an atmosphere of about 90% or more relative humidity.
An aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 39 ksi or more and exhibiting an average fatigue crack growth rate of not over 1.4.times.10.sup.-4 inch per cycle for growing a crack from about 1.7 inch to about 1 inch at a frequency of about 25 hertz and a stress ratio R of 0.1 and a substantially constant .DELTA.K of about 30 ksi.sqroot.in in an atmosphere of about 90% or more relative humidity.
A vehicular panel comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said sheet product having a long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 10 ksi.sqroot.in or more, or in both said properties.
Aircraft skin comprising an aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said sheet product having a long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 15 ksi.sqroot.in or more, or in both said properties.
Aircraft skin comprising an aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, less than 0.2% iron, less than 0.2% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet product having a minimum long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 15 ksi.sqroot.in or more, or in both said properties.
Aircraft skin comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.4 to 0.7% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said aluminum product having a long transverse yield strength of 39 ksi or more together with one or more of the following properties:
Aircraft skin comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy product having a long transverse yield strength of 39 ksi or more together with one or more of the following properties:
Aircraft fuselage skin comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said sheet having a long transverse yield strength of 40 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 15 ksi.sqroot.in or more, or in both said properties.
Aircraft fuselage skin comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy product having a long transverse yield strength of 40 ksi or more together with one or more of the following properties:
Aircraft fuselage skin comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 40 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 15 ksi.sqroot.in or more, or in both said properties.
Aircraft fuselage skin comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 3.9 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.4 to 0.8% manganese, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 40 ksi or more together with one or more of the following properties:
An aircraft fuselage, or fuselage portion, having reduced tear retarding auxiliary components, said fuselage or portion comprising fuselage skin comprising an aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said sheet having a long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 20 ksi.sqroot.in or more, or in both said properties.
An aircraft fuselage, or fuselage portion, having reduced tear retarding auxiliary components, said fuselage or portion comprising an aluminum alloy sheet or plate product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy product having a long transverse yield strength of 38 ksi or more together with one or more of the following properties:
An aircraft fuselage, or fuselage portion, having reduced tear retarding auxiliary components, said fuselage or portion comprising fuselage skin comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 20 ksi.sqroot.in or more, or in both said properties.
An aircraft fuselage, or fuselage portion, having reduced tear retarding auxiliary components, said fuselage or portion comprising fuselage skin comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 4 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.3 to 0.8% manganese, and containing not more than about 0.15% iron and not more than about 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a minimum long transverse yield strength of 39 ksi or more together with one or more of the following properties:
An aircraft having a member comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, and containing about 0.01 to 0.15% iron, about 0.01 to 0.15% silicon, the balance essentially aluminum and incidental elements and impurities, said sheet having a long transverse yield strength of 40 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 20 ksi.sqroot.in or more, or in both said properties.
An aircraft having a member comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, less than 0.2% iron, less than 0.2% silicon, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy product having a long transverse yield strength of 40 ksi or more together with one or more of the following properties:
An aircraft having skin material comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, less than 0.2% iron, less than 0.2% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 40 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 20 ksi.sqroot.in or more, or in both said properties.
An aircraft having skin material comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 4 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.4 to 0.7% manganese, and containing not more than about 0.15% iron and not more than about 0.12% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 40 ksi or more together with one or more of the following properties:
An aircraft having a fuselage skin, said fuselage skin comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, said sheet having a minimum long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K levels of 20 ksi.sqroot.in or more, or in both said properties.
An aircraft having a fuselage skin, said fuselage skin comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, and containing not more than about 0.15% iron and not more than about 0.12% silicon, the balance essentially aluminum and incidental elements and impurities, said aluminum alloy product having a long transverse yield strength of 40 ksi or more together with one or more of the following properties:
An aircraft having a fuselage skin, said fuselage skin comprising an aluminum alloy sheet product comprising an aluminum base alloy consisting essentially of, by weight, about 3.8 to 4.5% copper, about 1.2 to 1.8% magnesium, about 0.3 to 0.9% manganese, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 39 ksi or more and at least 5% improvement over 2024 in (a) T-L fracture toughness property, or (b) fatigue crack growth rate property at a .DELTA.K level of 20 ksi.sqroot.in or more, or in both said properties.
An aircraft having a fuselage skin, said fuselage skin comprising an aluminum alloy product comprising an aluminum base alloy consisting essentially of, by weight, about 4 to 4.5% copper, about 1.2 to 1.5% magnesium, about 0.4 to 0.7% manganese, and containing not more than about 0.15% iron and not more than about 0.12% silicon, the balance essentially aluminum and incidental elements and impurities, and a cladding layer comprising aluminum or an aluminum alloy different from said core alloy on one or more faces thereof, said sheet having a long transverse yield strength of 39 ksi or more together with one or more of the following properties:
Dependencies are inferred from the claim text.