Abstract: A process for fabricating a worked product or a monolithic multi-functional structural element comprising aluminium alloy includes a hot working step and at least one transformation step by cold plastic deformation after the hot transformation step. At least two zones of the structural element have imposed generalized average plastic deformations and the imposed deformations are different by at least 2%. Structural elements can be fabricated, particularly for aeronautical construction, with properties that are variable while their geometric characteristics are identical to those of existing components. The process is economic and controllable, and properties can be varied for parts not requiring any artificial ageing.

Abstract: A welded assembly of aluminum alloy part, in which (i) at least a first aluminum alloy part is procured in a solution heat treated, quenched, optionally cold worked, and naturally aged at ambient temperature or pre-aged temper, and at least a second aluminum alloy part, (ii) said parts are welded to obtain a welded assembly having a welded zone, (iii) cold working the entire welded zone between 0.3% and 5% is performed, (iv) the welded assembly thus cold worked undergoes post-weld aging to obtain a final metallurgical temper.

Abstract: The present disclosure concerns a method for assembling aluminum alloy parts, in which (i) at least a first aluminum alloy part is procured in a solution heat treated, quenched, optionally cold worked, and naturally aged at ambient temperature or pre-aged temper, and at least a second aluminum alloy part, (ii) said parts are welded to obtain a welded assembly having a welded zone, (iii) cold working the entire welded zone between 0.3% and 5% is performed, (iv) the welded assembly thus cold worked undergoes post-weld aging to obtain a final metallurgical temper.

Abstract: The present disclosure concerns a method for assembling aluminum alloy parts, in which (i) at least a first aluminum alloy part is procured in a solution heat treated, quenched, optionally cold worked, and naturally aged at ambient temperature or pre-aged temper, and at least a second aluminum alloy part, (ii) said parts are welded to obtain a welded assembly having a welded zone, (iii) cold working the entire welded zone between 0.3% and 5% is performed, (iv) the welded assembly thus cold worked undergoes post-weld aging to obtain a final metallurgical temper.

Abstract: A vertical casting process for an intermediate product, including the steps of (a) preparation of at least two aluminum based alloys, particularly a first alloy with composition P and a second alloy with composition T, (b) casting of the first alloy with composition P to a required height HP, and (c) casting of an additional required height HT of the alloy with composition T. The object of this invention is the manufacture of monolithic structural elements with working properties that are variable in at least one direction, and particularly bi-functional or multi-functional structural elements capable of performing at least two functions that are traditionally performed by two different parts.

Abstract: The present disclosure concerns a method for assembling aluminum alloy parts, in which (i) at least a first aluminum alloy part is procured in a solution heat treated, quenched, optionally cold worked, and naturally aged at ambient temperature or pre-aged temper, and at least a second aluminum alloy part, (ii) said parts are welded to obtain a welded assembly having a welded zone, (iii) cold working the entire welded zone between 0.3% and 5% is performed, (iv) the welded assembly thus cold worked undergoes post-weld aging to obtain a final metallurgical temper.

Abstract: A vertical casting process for an intermediate product, including the steps of (a) preparation of at least two aluminum based alloys, particularly a first alloy with composition P and a second alloy with composition T, (b) casting of the first alloy with composition P to a required height HP, and (c) casting of an additional required height HT of the alloy with composition T. The object of this invention is the manufacture of monolithic structural elements with working properties that are variable in at least one direction, and particularly bi-functional or multi-functional structural elements capable of performing at least two functions that are traditionally performed by two different parts.

Abstract: A process for fabricating a worked product or a monolithic multi-functional structural element comprising aluminium alloy includes a hot working step and at least one transformation step by cold plastic deformation after the hot transformation step. At least two zones of the structural element have imposed generalized average plastic deformations and the imposed deformations are different by at least 2%. Structural elements can be fabricated, particularly for aeronautical construction, with properties that are variable while their geometric characteristics are identical to those of existing components. The process is economic and controllable, and properties can be varied for parts not requiring any artificial ageing.

Abstract: The present invention relates to a method for producing Al—Zn—Cu—Mg type alloy plates comprising between 4 and 12% zinc, less than 4% magnesium and less than 4% copper, other elements?0.5% each, and the remainder aluminum. The method comprising hot rolling, solution heat-treatment, quenching, controlled stretching with permanent elongation greater than 0.5% and aging, wherein the elapsed time D between the end of quenching and the start of controlled stretching is less than 2 hours. The invention further relates to plates and products produced or capable of being produced using such methods.

Abstract: This invention relates to a process for manufacturing an aluminium alloy part with structural hardening as well as to structural members including monolithic structural members and to products prepared from such structural members. A suitable process of the present invention involves annealing in a linear furnace with a controlled temperature profile comprising at least two zones or groups of zones Z1, Z2. The length parallel to the axis of the linear furnace of each of the at least two zones or groups of zones Z1 and Z2 is generally at least about one meter.

Abstract: A process for forming a structure element, particularly an lower wing element of an aircraft, manufactured from a rolled, extruded or forged product made of an alloy of 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, remainder Al. The product is treated by solution heat treating, quenching, controlled tension to more than 1.5% permanent deformation and aging.

Abstract: Rolled, extruded or forged product made of an AlCuMg alloy processed by solution heat treatment, quenching and cold stretching, to be used in the manufacture of aircraft structural elements, with the following composition (% by weight):

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):

Abstract: Rolled product for use in the manufacture of aircraft structural elements, made of an AlCuMg alloy processed by solution heat treatment, quenching and cold stretching. The product has a composition consisting essentially of, in % by weight: Fe<0.15; Si<0.15; Cu:3.8-4.4; Mg:1-1.5; Mn:0.5-0.8; Zr:0.08-0.15; other elements: <0.05 each and <0.15 total. This product has a thickness of between 6 and 60 mm, with an ultimate tensile strength Rm(L) in the quenched and stretched temper >475 MPa and yield stress R0.2(L)>370 MPa, with a ratio Rm(L)/R0.2(L)>1.25.

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.

Abstract: An aircraft structural component, particularly a fuselage component, production method using rolled, extruded or forged products made of aluminum alloy with the following composition (% by weight):

Abstract: Rolled, extruded or forged product made of an AlCuMg alloy processed by solution heat treatment, quenching and cold stretching, to be used in the manufacture of aircraft structural elements, with the following composition (% by weight): 1 Fe<0.15 Si<0.15 Cu:3.8-4.4 Mg:1-1.5 Mn:0.5-0.8 Zr:0.08-0.

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.

Abstract: A metal sheet with a total thickness >0.5 mm comprising an AlCuMg aluminum alloy consisting essentially of Al and, in percent by weight:______________________________________ 3.5 < Cu < 5.0 1.0 < Mg < 2.0 Si < 0.25 Fe < 0.25 Mn < 0.55 ______________________________________all other elements: <0.25with 0<Mn-2Fe<0.2,optionally plated with another aluminum alloy with the thickness of the plating being no more than 12% of the total thickness of the sheet, the sheet having a recrystallization rate >50% at all points and a deviation in recrystallization rate between surface and mid-thickness <35%, the sheet having in the quenched and stretched state or in the quenched, stretched and annealed state, a deflection after machining to mid-thickness of a bar resting on two distant supports with a length l such that:fe<0.14l.sup.2,where f is the deflection expressed in micrometers, e being the thickness of the sheet in mm and l is the length of the bar in mm.

Abstract: A metal sheet with a total thickness>0.5 mm comprising an AlCuMg aluminum alloy consisting essentially of Al and, in percent by weight:3.5<Cu<5.01.0<Mg<2.0Si<0.25Fe<0.25Mn<0.55all other elements: <0.25with0<Mn-2Fe<0.2,optionally plated with another aluminum alloy with the thickness of the plating being no more than 12% of the total thickness of the sheet, the sheet having a recrystallization rate>50% at all points and a deviation in recrystallization rate between surface and mid-thickness<35%, the sheet having in the quenched and stretched state or in the quenched, stretched and annealed state, a deflection after machining to mid-thickness of a bar resting on two distant supports with a length l such that:fe<0.14 1.sup.2,where f is the deflection expressed in micrometers, e being the thickness of the sheet in mm and l is the length of the bar in mm.