Constellium Issoire

Pechiney Rhenalu

Other

Alcan Rhenalu

Constellium France

Alcan Rhenalu/constellium France

Constellium Rolled Products Ravenswood, LLC

Bernard Bes

Timothy Warner

Philippe Jarry

Jean-Christophe Ehrstrom

Frank Eberl

Ronan Dif

Herve Ribes

Christophe Sigli

Vic Dangerfield

Juliette Chevy

Philippe Lassince

Alex Cho

Gaelle Pouget

Hervé Ribes

Gaëlle Pouget

Ricky Whelchel

Alireza Arbab

Fanny Mas

Mathieu Revil-baudard

Jérome Pignatel

The invention concerns a process to manufacture a flat-rolled product, notably for the aeronautic industry containing aluminum alloy, in which, notably a flattening and/or stretching is performed with a cumulated deformation of at least 0.5% and less than 3%, and a short heat-treatment is performed in which the sheet reaches a temperature between 130&#xb0; C. and 170&#xb0; C. for a period of 0.1 to 13 hours. The invention notably makes it possible to simplify the forming process of fuselage skins and to improve the balance between static mechanical strength properties and damage tolerance properties.

Transformation process of Al&#x2014;Cu&#x2014;Li alloy sheets

The invention relates to a plate with a thickness of 0.5 to 9 mm with an essentially recrystallized granular structure, made from an alloy based on aluminum, comprising 2.8 to 3.2% by weight Cu, 0.5 to 0.8% by weight Li, 0.1 to 0.3% by weight Ag, 0.2 to 0.7% by weight Mg, 0.2 to 0.6% by weight Mn, 0.01 to 0.15% by weight Ti, a quantity of Zn below 0.2% by weight, a quantity of Fe and Si of less than or equal to 0.1% by weight each, and unavoidable impurities to a proportion of less than or equal to 0.05% by weight each and 0.15% by weight in total, said plate being obtained by a method comprising casting, homogenization, hot rolling and optionally cold rolling, solution heat treatment, quenching and aging. The plates according to the invention are advantageous in particular for the manufacture of aircraft fuselage panels.

Isotropic plates made from aluminum-copper-lithium alloy for manufacturing aircraft fuselages

The invention concerns a process to manufacture a flat-rolled product, notably for the aeronautic industry containing aluminum alloy, in which, notably a flattening and/or stretching is performed with a cumulated deformation of at least 0.5% and less than 3% and a short heat-treatment is performed in which the sheet reaches a temperature between 130&#xb0; C. and 170&#xb0; C. for a period of 0.1 to 13 hours. The invention notably makes it possible to simplify the forming process of fuselage skins and to improve the balance between static mechanical strength properties and damage tolerance properties.

The invention relates to a method for manufacturing a thin sheet having a thickness of 0.5 to 3.3 mm and an essentially non-recrystallized structure made of aluminum-based alloy.

Thin sheets made of an aluminium-copper-lithium alloy for producing airplane fuselages

The invention relates to a rolled product with state T351, having thickness of between 15 and 50 mm, made from aluminum alloy having the following composition, in % by weight, Cu: 3.85-4.15; Mg: 0.95-1.25; Mn: 0.45-0.57; Zr: 0.09-0.16; Ti: 0.005-0.1; Fe: &#x3c;0.070; Si: &#x3c;0.060; with Cu+Mg&#x2264;5.15; other lesser elements 0.05 each and less than 0.15 in total, the remainder being aluminum.

Lower wing skin metal with improved damage tolerance properties

A method for producing a rolled product 0.5 to 10 mm thick made from an aluminum alloy comprising, in particular, copper and lithium, in which, after solution annealing and quenching, a short heat treatment is carried out in which the sheet reaches a temperature of between 145&#xb0; C. and 175&#xb0; C. for 0.1 to 45 minutes, the speed of heating being between 3 and 600&#xb0; C./min. The sheet obtained at the end of the method according to the invention has high corrosion resistance and is capable of being shaped for producing a structural element for an aircraft, in particular an aircraft fuselage skin.

Method for transforming Al&#x2014;Cu&#x2014;Li alloy sheets improving formability and corrosion resistance

An aluminum alloy comprising 2.1 to 2.8 wt. % Cu, 1.1 to 1.7 wt. % Li, 0.1 to 0.8 wt. % Ag, 0.2 to 0.6 wt. % Mg, 0.2 to 0.6 wt. % Mn, a content of Fe and Si less or equal to 0.1 wt. % each, and a content of unavoidable impurities less than or equal to 0.05 wt. % each and 0.15 wt. % total, and the alloy being substantially zirconium free.

High fracture toughness aluminum-copper-lithium sheet or light-gauge plates suitable for fuselage panels

The invention relates to a work-hardened product, particularly a rolled, extruded or forged product, made of an alloy with the following composition (% by weight): Cu 3.8-4.3; Mg 1.25-1.45; Mn 0.2-0.5; Zn 0.4-1.3; Fe&#x3c;0.15; Si&#x3c;0.15; Zr&#x2266;0.05; Ag&#x3c;0.01, other elements &#x3c;0.05 each and &#x3c;0.15 total, remainder Al, treated by dissolution, quenching and cold strain-hardening, with a permanent deformation of between 0.5% and 15%, and preferably between 1.5% and 3.5%. Cold strain-hardening can be achieved by controlled tension and/or cold transformation, for example rolling, die forging or drawing. This cladded metal plate type product is a suitable element to be used as aircraft fuselage skin.

Aircraft structural member made of an Al-Cu-Mg alloy

The invention relates to alloys and associated products which are laminated, extruded or forged in Al&#x2014;Zn&#x2014;Mg&#x2014;Cu alloy. Alloys of the invention generally comprise (in mass percentage):

Al-Zn-Mg-Cu alloys and products with improved ratio of static mechanical characteristics to damage tolerance

The invention relates to a work-hardened product, particularly a rolled, extruded or forged product, made of an alloy with the following composition (% by weight):

New alloys for potential use in applications such as in lower wing skins and fuselage skins are disclosed. Specifically, Mn-free 2&#xd7;24 alloys potentially suitable for thick plate and thin plate and sheet applications are believed to be novel and to provide unexpectedly superior properties.

AlCuMg alloys with high damage tolerance suitable for use as structural members in aircrafts

Clad sheet made up of a core sheet and a cladding layer on one or two core sheet surfaces. The core sheet is formed of an alloy having the composition (% by weight) Si: 0.7-1.3, Mg: 0.6-1.2, Cu: 0.5-1.1, Mn: 0.15-1.0, Zn<0.5, Fe<0.5, Zr<0.2, Cr<0.25, other elements <0.05 each and <0.15 total, the remainder aluminum. The cladding is formed of an AlZn alloy having a thickness of between 1 and 15% of the clad sheet thickness, having the composition (% by weight) Zn: 0.25-0.7, Fe<0.40, Si<0.40, Cu, Mn, Mg, V or Ti <0.10, other elements <0.05 each and 0.15 total.

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Seyssins, France

Bernard Bes