Patent ID: 6972110
Filing Date: 2005-12-06
Classification: B22D,C22C,C22F

Abstract:
1. An aluminum alloy aerospace structural component that in solution heat treated, quenched and artificially aged condition, exhibits an improved combination of strength and fracture toughness, said alloy consisting essentially of: 7 to 9.5 wt. % Zn; 1.3 to 1.68 wt. % Mg; 1.3 to 1.9 wt. % Cu; one or more elements present selected from the group consisting of: up to about 0.4 wt. % Zr, up to about 0.4 wt. % Sc and up to about 0.3 wt. % Hf; said alloy optionally containing one or more of up to about 0.06 wt. % Ti, up to about 0.03 wt. % Ca, up to about 0.03 wt. % Sr, up to about 0.002 wt. % Be, said alloy containing less than 0.1 wt. % Mn and less than 0.05 wt. % Cr, the balance being Al, incidental elements and impurities, wherein said aerospace structural component is selected from the group consisting of a spar member, rib member, web member, stringer member, wing panel member, wing skin member, fuselage frame member, floor beam member, bulkhead member and landing gear beam member.