Constellium Issoire

Alcan Rhenalu

Constellium France

Airbus Operations Gmbh

C-tec Constellium Technology Center

Constellium Rolled Products Ravenswood, LLC

Jean-Christophe Ehrstrom

Timothy Warner

Bernard Bes

Gaelle Pouget

Ricky Whelchel

Diana Koschel

Erembert Nizery

Armelle Danielou

Christophe Sigli

Frank Eberl

Bechir Chehab

Henri Gérard

Ronan Dif

Pablo Lorenzino

Sjoerd Van Der Veen

Juliette Chevy

Vic Dangerfield

Sylvie Arsene

David Dumont

Alireza Arbab

Julien Laye

Hervé Ribes

Gaëlle Pouget

Francois Lemaitre

Bernard Grange

Vincent Hochenedel

Carla Da Fonseca Barbatti

Laurent Cervi

Michelle Salvia

Melanie Ollat

François Lemaitre

Herve Ribes

The invention relates to a rolled product made of aluminum alloy with a thickness of at least 50 mm comprising (in weight %): Zn 6.9-7.5; Mg 1.8-2.2; Cu 1.8-2.2, where the sum Cu+Mg is between 3.8 and 4.2; Zr 0.04-0.14; Mn 0-0.1; Ti 0-0.15; V 0-0.1; Fe ≤0.15; If ≤0.15; impurities ≤0.05 each and ≤0.15 total, balance aluminum. The invention also relates to the method of manufacturing such a product. The products according to the invention are particularly advantageous because they have a very favorable compromise between static mechanical strength, toughness and environmental-assisted cracking performance under conditions of high stress and humid environment.

Al—Zn—Cu—Mg alloys with high strength and method of fabrication

A method for thermomechanical treatment of wrought products made of a 2000 series aluminum alloy comprising, in % by weight, Cu 3.5-5.8; Mg 0.2-1.5; Mn≤0.9; Fe≤0.15; Si≤0.15; Zr≤0.25; Ag≤0.8; Zn≤0.8; Ti 0.02-0.15; unavoidable impurities≤0.05 each and ≤0.15 total; remainder aluminum, enabling an improvement in the resistance to corrosion under stress. It includes a tempering consisting of two sequences. The first sequence is defined by a maximum temperature Tcomprised between 130° C. and 180° C. and by a hold time at a temperature comprised between 130° C. and 180° C. which equates to an equivalent duration tcalculated at 160° C. comprised between 10 h and 80 h. The second sequence is defined by a temperature T(t) lower than Tand a hold time tat a temperature comprised between 100° C. and 130° C., which equates to an equivalent time tcalculated at 160° C. such that t° comprised between 0.3% and 15% of the equivalent duration t° calculated for the first sequence.

Wrought products made of 2XXX alloy having an optimized corrosion resistance, and method for obtaining same

A process for manufacturing a bimetallic part by means of a first component formed by a first aluminum alloy and a second component formed by a second aluminum alloy, said process involving: assembling the first component and the second component to obtain an assembled part; applying a thermal treatment to the assembled part at a temperature of 100 to 250° C., the thermal treatment causing the assembled part to deform, in particular as a result of a metallurgical deformation by a precipitation of hardening phases of the first component and/or the second component; cooling the part to ambient temperature, upon which the part remains deformed. The process involves, prior to the assembling step, an estimation of the degree of deformation that the assembled part will undergo under the effect of the thermal treatment.

Process for manufacturing a bimetallic part using a dilation-causing thermal treatment

The invention relates to a thin metal sheet which is made of an alloy based on substantially recrystallized aluminum and which has a thickness of 0.25 to 12 mm, the alloy comprising, in percent by weight, Cu 3.4-4.0; Mg 0.5-0.8; Mn 0.1-0.7; Fe #0.15; Si #0.15; Zr #0.04; Ag #0.65; Zn #0.5; inevitable impurities #0.05 each and #0.15 in total, the remainder consisting of aluminum. The invention also relates to a process for manufacturing such a metal sheet and to the use thereof as a fuselage panel or sheet metal for the production of composite products such as fiber metal laminates (FML) for wing or fuselage applications in the aeronautical industry.

Metal sheet made of high-strength 2XXX alloy for an aircraft fuselage

The invention concerns an extruded, rolled and/or forged aluminum-based alloy product having a thickness of at least 25 mm comprising (in weight %): Zn 6.70-7.40; Mg 1.50-1.80; Cu 2.20-2.60, with a Cu to Mg ratio of at least 1.30; Zr 0.04-0.14; Mn 0-0.5; Ti 0-0.15; V 0-0.15; Cr 0-0.25; Fe 0-0.15; Si 0-0.15; impurities ≤0.05 each and ≤0.15 total. The invention also concerns a method of making such a product. Products according to the invention are particularly advantageous because they exhibit simultaneously a low sensitivity to environmentally assisted cracking under conditions of high stress and humid environment, high strength and high toughness properties.

Al—Zn—Cu—Mg alloys and their manufacturing process

The invention relates to the method for manufacturing a rolled product of variable thickness made of heat-treatable aluminum alloy in which hot rolling is performed to achieve a variation in thickness of at least 10% lengthwise between the thickest part and the thinnest part; the rolled product of variable thickness obtained undergoes solution heat-treatment and quenching with permanent set of at least 1% in the thickest part before natural or artificial ageing. The products obtained according to the invention exhibit improved mechanical strength of at least 5% in the thinnest part and improved fracture toughness of at least 15% in the thickest part. The products according to the invention are notably useful in the fabrication of aircraft upper or lower wing skins the 'buy to fly' ratio and the properties are simultaneously improved.

Method for manufacturing a structural element having a variable thickness for aircraft production

Provided herein is a method for manufacturing a worked product comprising a fiber sensor therein. Also provided is a wrought product comprising a fiber sensor as well as structural elements and other products including fuselage skin and a wing panel.

Structrual element made of an aluminum alloy including an optical sensor

A structural member comprising at least two aluminum alloy parts displaying different property balances, said at least two parts being welded and wherein one of said parts either is (i) selected from an aluminum alloy different from the other of said at least two parts and/or (ii) is selected from an initial temper different from the other of said at least two parts, and wherein at least one of said at least two parts has been pre-aged prior to being welded, and, wherein said structural member has undergone a post-welding thermal treatment conferring a final temper to each of said at least two parts. The parts are advantageously welded by friction stir welding. Another subject of the invention is a method for manufacturing a structural member.

Welded structural member and method and use thereof

In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length.

Structural element and method of manufacture

A process for making Al&#x2014;Zn&#x2014;Mg alloy products, and products formed according to such processes are disclosed. The present invention provides a product having an improved compromise between mechanical characteristics and corrosion strength.

Simplified method for making rolled Al&#x2014;Zn&#x2014;Mg alloy products, and resulting products

A method for manufacturing aluminium alloy parts with precipitation hardening including friction stir welding of at least two elements made from the same alloy or different alloys, solution heat treatment, and quenching of welded parts, in which the elements are subjected to heat treatment before welding at temperature T for at least 2t, tbeing defined as the minimum treatment duration at temperature T leading to a specific melting peak energy defined by AED equal to less than 1 J/g. A method according to the invention substantially avoids an increase in the grain size following solution heat treatment after welding. The invention further relates to novel aluminum materials as well as uses therefor.

Manufacturing method for friction welded aluminum alloy parts

A Glare type composite laminated sandwich panel comprising (i) aluminum (ii) glass fibre with adhesive (iii) aluminum is disclosed. According to the present invention, at least one of the aluminum sheets is preferably made of an aluminum non-heat treatable alloy type Al&#x2014;Mg with a magnesium content of between 4 and 6%. These sandwich panels have mechanical characteristics similar to sandwich panels comprising sheets with a heat treatable alloy. Panels of the present invention further generally have better corrosion resistance and are less expensive than those made with heat treatable alloys such as 2xxx and 7xxx type alloys.

Composite laminated aluminum-glass fiber sandwich panels

Growing community of inventors

Echirolles, France

Jean-Christophe Ehrstrom