Aircraft structure element made of an Al-Cu-Mg- alloy
AssigneePechiney Rhenalu
InventorsTimothy Warner, Philippe Lassince, Philippe Lequeu
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Abstract
The purpose of the invention is a structure element, particularly an lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy with composition (% by weight): Cu=4.6-5.3, Mg=0.10-0.50, Mn=0.15-0.45, Si<0.10, Fe<0.15, Zn<0.20, Cr<0.10, other elements <0.05 each and <0.15 total, the remainder being Al treated by solution heat treating, quenching, controlled tension to more than 1.5% permanent deformation and aging.
Claims24
Structure element, particularly a lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy with composition (% by weight):
- Cu=4.6-5.3, Mg=0.10-0.50, Mn=0.15-0.45, Si<0.10, Fe<0.15, Zn<0.20, Cr<0.10, other elements <0.05 each and <0.15 total, the remainder being Al treated by solution heat treating, quenching, controlled tension to more than 1.5% permanent deformation and aging:
Manufacturing process for a structure element comprising:
- a) casting a plate or a billet with the following composition,
- Cu=4.6-5.3, Mg=0.10-0.50, Mn=0.15-0.45, Si<0.10, Fe<0.15, Zn<0.20, Cr<0.10, other elements are <0.05 each and <0.15 total, the remainder being aluminum.
- b) homogenization of this plate or billet,
- c) hot transformation of this plate by rolling or of this billet by extrusion or forging to obtain a product thicker than 10 mm,
- d) quenching of the hot transformed product,
- e) solution heat treating of this product, preferably at a temperature of less than 10° C. at the incipient melting temperature of the alloy,
- f) controlled tension of the product to obtain a permanent deformation of more than 1.5%,
- g) aging of the product at a temperature greater than 160° C., possibly together with forming,
- h) machining of the product formed until the final shape of the structure elements.
Dependencies are inferred from the claim text.