ALUMINUM-MAGNESIUM-SILVER BASED ALLOYS
Al—Mg—Ag wrought products and methods of making such products useful in aircraft applications. The Al—Mg—Ag wrought products have improved strength when compared to traditional AA5XXX alloys. The alloys may comprise from about 3.5 to about 10 weight percent Mg, from about 0.05 to about 0.5 weight percent Ag, from about 0.01 to about 1.0 weight percent Mn, from about 0.01 to about 0.15 weight percent Zr, and the remainder Al and incidental impurities. In addition, from about 0.05 to about 0.4 weight percent Sc may be added to further improve the strength characteristics.
1 . An aluminum alloy consisting essentially of from about 3.5 to about 10 weight percent Mg, from about 0.05 to about 0.5 weight percent Ag, from about 0.01 to about 1.0 weight percent Mn, from about 0.01 to about 0.15 weight percent Zr, the remainder aluminum and incidental elements and impurities.
2 . The aluminum alloy of claim 1 , wherein the alloy consists essentially of from about 4.0 to about 7.0 weight percent Mg.
3 . The aluminum alloy of claim 1 , wherein the alloy consists essentially of from about 0.2 to about 0.4 weight percent Ag.
4 . The aluminum alloy of claim 1 , wherein the alloy consists essentially of from about 0.5 to about 0.8 weight percent Mn.
5 . The aluminum alloy of claim 1 , wherein the alloy consists essentially of from about 0.07 to about 0.13 weight percent Zr.
6 . The aluminum alloy of claim 1 , wherein the alloy further comprises from about 0.1 about about 1.5 weight percent Cu and from about 0.1 to about 1.5 weight percent Zn.
7 . The aluminum alloy of claim 1 , wherein the alloy further comprises from about 0.05 to about 0.2 weight percent Sc.
8 . The aluminum alloy of claim 1 , wherein the alloy is in the form of an extruded product.
9 . The aluminum alloy of claim 1 , wherein the alloy is in the form of a sheet or plate product.
10 . The aluminum alloy of claim 1 , wherein the alloy is in the form of a forged product.
11 . An aircraft structural member comprising the aluminum alloy of claim 1 .
12 . A fuselage stringer comprising the aluminum alloy of claim 1 .
13 . A fuselage sheet member comprising the aluminum alloy of claim 1 .
14 . A wing rib member comprising the aluminum alloy of claim 1 .
15 . An extruded alloy product comprising an aluminum alloy consisting essentially of from about 3.5 to about 10.0 weight percent Mg, from about 0.05 to about 0.5 weight percent Ag, from about 0.01 to about 1.0 weight percent Mn, from about 0.01 to about 0.15 weight percent Zr, maximum 0.15 weight percent Fe, maximum 0.15 weight percent Si, and the remainder aluminum and incidental elements and impurities.
16 . The extruded alloy product of claim 15 , wherein the alloy consists essentially of from about 4.0 to about 7.0 weight percent Mg.
17 . The extruded alloy product of claim 15 , wherein the alloy consists essentially of from about 0.2 to about 0.4 weight percent Ag.
18 . The extruded alloy product of claim 15 , wherein the alloy consists essentially of from about 0.5 to about 0.8 weight percent Mn.
19 . The extruded alloy product of claim 15 , wherein the alloy consists essentially of from about 0.07 to about 0.13 weight percent Zr.
20 . The extruded alloy product of claim 15 , wherein the alloy further comprises from about 0.1 to about 1.5 weight percent Cu and from about 0.1 to about 1.5 weight percent Zn.
21 . The extruded alloy product of claim 15 , wherein the alloy further comprises from about 0.05 to about 0.2 weight percent Sc.
22 . An aircraft stringer comprising the extruded alloy product of claim 15 .
23 . An aircraft floor beam comprising the extruded alloy product of claim 15 .
24 . An aircraft frame comprising the extruded alloy product of claim 15 .
25 . A rolled alloy product comprising an aluminum alloy consisting essentially of from about 3.5 to about 10.0 weight percent Mg, from about 0.05 to about 0.5 weight percent Ag, from about 0.01 to about 1.0 weight percent Mn, from about 0.01 to about 0.15 weight percent Zr, maximum 0.15 weight percent Fe, maximum 0.15 weight percent Si, and the remainder aluminum and incidental elements and impurities.
26 . The rolled alloy product of claim 25 , wherein the alloy consists essentially of from about 4.0 to about 7.0 weight percent Mg.
27 . The rolled alloy product of claim 25 , wherein the alloy consists essentially of from about 0.2 to about 0.4 weight percent Ag.
28 . The rolled alloy product of claim 25 , wherein the alloy consists essentially of from about 0.5 to about 0.8 weight percent Mn.
29 . The rolled alloy product of claim 25 , wherein the alloy consists essentially of from about 0.07 to about 0.13 weight percent Zr.
30 . The rolled alloy product of claim 25 , wherein the alloy further comprises from about 0.1 to about 1.5 weight percent Cu and from about 0.1 to about 1.5 weight percent Zn.
31 . The rolled alloy product of claim 25 , wherein the alloy further comprises from about 0.05 to about 0.2 weight percent Sc.
32 . An aircraft fuselage sheet comprising the rolled alloy product of claim 25 .
33 . An aircraft stringer comprising the rolled alloy product of claim 25 .
34 . An aircraft frame comprising the rolled alloy product of claim 25 .