Aircraft stringer material and method for producing the same

Details Aircraft stringer material and method for producing the same Aircraft stringer material and method for producing the same

1980-07-30

1983-10-18

Dean, R.

Metal treatment

Compositions

Heat treating

148 115Q, 148 127A, 148417, 148439, C22F 104

Patent

active

044103700

ABSTRACT:
An aircraft stringer material having high strength, small grain size, good resistance to stress corrosion cracking and a very high degree of workability is produced from an aluminum base alloy consisting essentially of 5.1 to 8.1 wt. % Zn, 1.8 to 3.4 wt. % Mg, 1.2 to 2.6 wt. % Cu, up to 0.20 wt. % Ti and at least one of 0.18 to 0.35 wt. % Cr and 0.05 to 0.25 wt. % Zr, the balance being aluminum and impurities, by a production method characterized by a special annealing step including rapid heating to a temperature of 320.degree. to 500.degree. C. at a heating rate exceeding 11.degree. C./min.
Further, a corrosion-resistant stringer material is produced in a manner very similar to the above production method, using the above aluminum alloy as a core and AA7072 alloy as cladding.

REFERENCES:
patent: 4305763 (1981-12-01), Quist et al.

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