Patent ID: 7610669
Filing Date: 2009-11-03
Classification: C22C,C22F,Y10T

Abstract:
1. A method for manufacturing an aeronautical member, comprising the steps of: a.) providing an aluminum alloy plate with a predetermined thickness, said plate having been stretched after quenching and having been brought to a first temper selected from the group consisting of T4, T73, T74 and T76, wherein said aluminum alloy plate is produced from a AA7xxx-series aluminium alloy having a composition consisting of, in weight percent: optionally one or more elements selected from: the total of the optional elements not exceeding 0.6, incidental impurities each <0.05, total <0.20; the balance aluminium, b.) shaping said alloy plate to obtain a predetermined shaped structure having a pre-machining thickness in the range of 10 to 220 mm, wherein said shaping comprises cold forming, wherein said cold forming comprises bending said alloy plate in said first temper selected from the group consisting of T4, T73, T74 and T76 to form the shaped structure having a built-in radius, c.) heat-treating said shaped structure, wherein said heat-treating comprises artificially aging said shaped structure to a second temper selected from the group consisting of T6, T79, T78, T77, T76, T74, T73 or T8, d.) machining said shaped structure to obtain an integrated monolithic aluminum structure as said aeronautical member for an aircraft, wherein said machining of said shaped structure occurs after said artificial ageing.