Aircraft stringer material and method for producing the same
US4410370A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jul 30, 1980 |
| Grant date | Oct 18, 1983 |
| Priority date | — |
| Expiry date | Jul 30, 2000 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC22F1/053
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.