Clad 2XXX-series aerospace product

1. A rolled composite aerospace product comprising a 2XXX-series core layer and a 6XXX-series aluminium alloy clad layer coupled to at least one surface of the 2XXX-series core layer, wherein the 6XXX-series aluminium alloy comprises, in wt. %, Si 0.3% to 1.0%, Mg 0.3% to 1.1%, Mn 0.04% to 1.0%, Fe 0.03% to 0.4%, Cu up to 0.10%, Cr up to 0.25%, V up to 0.2%, Zr up to 0.2%, Zn up to 0.5%, Ti up to 0.1%, unavoidable impurities each <0.05%, total <0.15%, balance aluminium,

wherein the 2XXX-series core layer is in a T3, T351, T39, T8 or T851 temper; and

wherein the 6XXX-series aluminium alloy clad layer is in a T4 or T6 temper.

2. The rolled composite aerospace product according to claim 1 , wherein the 6XXX-series aluminium alloy has a Si-content in a range of 0.4% to 0.9%.

3. The rolled composite aerospace product according to claim 1 , wherein the 6XXX-series aluminium alloy has a Mg-content in a range of 0.40% to 0.90%.

4. The rolled composite aerospace product according to claim 1 , wherein the 6XXX-series aluminium alloy has a Mn-content in a range of 0.25% to 1.0%.

5. The rolled composite aerospace product according to claim 1 , wherein the 6XXX-series aluminium alloy clad layer is coupled by means of roll bonding to the at least one surface of the 2XXX-series core layer.

6. The rolled composite aerospace product according to claim 1 , wherein the 6XXX-series aluminium alloy clad layer has a thickness in the range of 1% to 20%, and preferably 1% to 10%, of the total thickness of the rolled composite aerospace product.

7. The rolled composite aerospace product according to claim 1 , consisting of a 2XXX-series core layer and a 6XXX-series aluminium alloy clad layer coupled to one surface of the 2XXX-series core layer.

8. The rolled composite aerospace product according to claim 1 , consisting of a 2XXX-series core layer and a 6XXX-series aluminium alloy clad layer coupled to both surfaces of the 2XXX-series core layer.

9. The rolled composite aerospace product according to claim 1 , wherein the 2XXX-series alloy of the core layer has a composition of, in wt. %,

Cu 1.9% to 7.0%,

Mg 0.30% to 1.8%,

Mn up to 1.2%,

Si up to 0.40%,

Fe up to 0.40%,

Cr up to 0.35%,

Zn up to 1.0%,

Ti up to 0.15%,

Zr up to 0.25%,

V up to 0.25%,

Li up to 2.0%,

Ag up to 0.80%,

Ni up to 2.5%,

balance being aluminium and impurities.

10. The rolled composite aerospace product according to claim 1 , wherein the 2XXX-series core layer is from the 2×24-series alloy.

11. The rolled composite aerospace product according to claim 1 , wherein the rolled composite aerospace product has a total thickness of 0.8 mm to 50.8 mm.

12. The rolled composite aerospace product according to claim 1 , wherein the rolled composite aerospace product is a plate product.

13. The rolled composite aerospace product according to claim 1 , wherein the rolled composite aerospace product is a sheet product.

14. The rolled composite aerospace product according to claim 1 , wherein the rolled composite aerospace product is an aerospace structural part.

15. A method of manufacturing a rolled composite aerospace product according to claim 1 , comprising the steps of:

(a) providing an ingot of a 2XXX-series aluminium alloy for forming the core layer of the composite aerospace product;

(b) homogenizing the ingot of the 2XXX-series aluminium alloy at a temperature in the range of 400° C. to 505° C. for at least 2 hours;

(c) providing an ingot or rolled clad liner of a 6XXX-series aluminium alloy for forming an outer clad layer on the 2XXX-series core aluminium alloy;

(d) homogenizing the ingot of the 6XXX-series aluminium alloy at a temperature in the range of at least 480° C., for at least 0.5 hour;

(e) roll bonding the 6XXX-series aluminium alloy to the 2XXX-series core alloy to form a roll bonded product, and optionally followed by cold rolling;

(f) solution heat-treating the roll bonded product at a temperature in the range of 450° C. to 505° C.;

(g) cooling of the solution heat-treated roll bonded product to below 100° C.;

(h) optionally stretching of the solution heat-treated and cooled roll bonded product; and

(i) ageing of the 2XXX-series core alloy of the cooled roll bonded product.

16. The method according to claim 15 , wherein the method further comprises forming of the solution heat-treated and cooled roll bonded product, and optionally also being stretched, in a forming process into a predetermined shape product.

17. The method according to claim 15 , wherein a forming step (j) is performed after the ageing step (i).

18. The method according to claim 16 , wherein the forming step (j) and the ageing step (i) are combined in a forming step at elevated temperature.