High strength al-cu-mg-ag-si alloy for structural applications

Abstract

The present invention relates generally to aluminum-copper-magnesium based alloys and products, and more particularly to aluminum-copper-magnesium-Silver-Silicon based alloys and products particularly suitable for aircraft structural applications and military vehicle structural applications requiring very high strength and ductility.

I claim: 
     
         1 . An alloy comprising from about 4.0-6.0 wt. % copper, from about 0.1-1.8 wt. % magnesium, from about 0.0-0.8 wt. % silver, from about 0.0-0.8 wt. % manganese, from about 0.1-1.2 silicon, and from about 0.0-0.12 titanium and the balance being aluminum and incidental elements and impurities. 
     
     
         2 . The alloy of  claim 1 , wherein said incidental element and impurities can includes iron. 
     
     
         3 . The alloy of  claim 1 , further comprising one or more dispersoid forming elements selected from the group consisting of chromium, zirconium, scandium and vanadium and combinations thereof. 
     
     
         4 . The alloy of  claim 1 , further comprising chromium in an amount of up to 0.8 wt. %, scandium in an amount up to 0.8 wt. %, and vanadium in an amount of up to 0.2 wt. % either in addition to, or instead of titanium. 
     
     
         5 . The alloy of  claim 1  exhibit very high strength when the alloy is processed to wrought product for engineering structural applications having surprisingly high strength in T6 temper product (i.e., no cold work or very low amount of cold work prior to final age strengthening step on the product of cold water quenched after solution heat treatment) 
     
     
         6 . The alloy of  claim 1  is suitable for T8 temper application with even more pronounced high strength capability for engineering structural applications.