Abstract: 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° C. and 170° 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.

Abstract: 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.

Abstract: 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° C. and 170° 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.

Abstract: A method for manufacturing a brushed rolled product made from Al—Cu—Li alloy with a thickness of less than 12 mm, including the steps of producing a rolled product, solution heat treatment and quenching, stress relieving, optionally tempering, and brushing, wherein the brushing tool applies a force to the rolled product generating residual compressive stresses at the surface of the brushed product; eliminates a thickness of at least 9 ?m from the surface of the non-brushed rolled product; wherein the brushing step comprises at least one circular brushing motion. The rolled product obtained by the method according to the invention is advantageous. The use of such a product in an aircraft fuselage panel is advantageous.

Abstract: 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.

Abstract: 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° C. and 175° C. for 0.1 to 45 minutes, the speed of heating being between 3 and 600° 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.

Abstract: The present invention relates to extruded, rolled and/or forged products. Also provided are methods of making such products based on aluminum alloy wherein a liquid metal bath is prepared comprising 2.0 to 3.5% by weight of Cu, 1.4 to 1.8% by weight of Li, 0.1 to 0.5% by weight of Ag, 0.1 to 1.0% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.2 to 0.6% by weight of Mn and at least one element selected from Cr, Sc, Hf and Ti, the quantity of said element selected, being 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti, the remainder being aluminum and inevitable impurities. The products and methods of the present invention offer an advantageous compromise between static mechanical strength and damage tolerance and are useful in aeronautical design.

Abstract: The invention concerns a process to manufacture a flat-rolled product, notably for the aeronautic industry containing aluminum alloy comprising 2.1% to 3.9% Cu by weight, 0.7% to 2.0% Li by weight, 0.1% to 1,0% Mg by weight, 0% to 0.6% Ag by weight, 0% to 1% Zn by weight, at least 0.20% Fe +Si by weight, at least one element chosen from Zr, Mn, Cr, Sc, Hf and Ti, the quantity of said element, if chosen, being 0.05% to 0.18% by weight for Zn, 0.1% to 0.6% by weight for Mn, 0.05% to 0.3% by weight for Cr, 0.02% to 0.2% by weight for Sc, 0.05% to 0.5% by weight for Hf and 0.01% to 0.15% by weight for Ti, the other elements at most 0.05% by weight each and 0.15% by weight in total, the rest being aluminum, 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° C. and 170° C. for a period of 0.1 to 13 hours.

Abstract: The present invention relates to extruded, rolled and/or forged products. Also provided are methods of making such products based on aluminum alloy wherein a liquid metal bath is prepared comprising 2.0 to 3.5% by weight of Cu, 1.4 to 1.8% by weight of Li, 0.1 to 0.5% by weight of Ag, 0.1 to 1.0% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.2 to 0.6% by weight of Mn and at least one element selected from Cr, Sc, Hf and Ti, the quantity of said element selected, being 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti, the remainder being aluminum and inevitable impurities. The products and methods of the present invention offer an advantageous compromise between static mechanical strength and damage tolerance and are useful in aeronautical design.

Abstract: 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.

Abstract: The invention concerns the method for producing a rolled product 0.5 to 10 mm thick made from an aluminium 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° C. and 175° C. for 0.1 to 45 minutes, the speed of heating being between 3 and 600° 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.

Abstract: The invention concerns a sheet 0.5 to 8 mm thick made from aluminium alloy. The sheet can be obtained by a method comprising casting, homogenising, hot rolling and optionally cold rolling, solution heat treatment, quenching and tempering, the composition and the tempering being combined in such a way that the elasticity limit in the longitudinal direction Rp0.2(L) is between 395 and 435 MPa. A sheet according to the invention is particularly advantageous for producing aircraft fuselage panels.

Abstract: 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.

Abstract: 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.

Abstract: The present invention relates to extruded, rolled and/or forged products. Also provided are methods of making such products based on aluminum alloy wherein a liquid metal bath is prepared comprising 2.0 to 3.5% by weight of Cu, 1.4 to 1.8% by weight of Li, 0.1 to 0.5% by weight of Ag, 0.1 to 1.0% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.2 to 0.6% by weight of Mn and at least one element selected from Cr, Sc, Hf and Ti, the quantity of said element selected, being 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti, the remainder being aluminum and inevitable impurities. The products and methods of the present invention offer an advantageous compromise between static mechanical strength and damage tolerance and are useful in aeronautical design.

Abstract: The present invention relates to extruded, rolled and/or forged products. Also provided are methods of making such products based on aluminum alloy wherein a liquid metal bath is prepared comprising 2.0 to 3.5% by weight of Cu, 1.4 to 1.8% by weight of Li, 0.1 to 0.5% by weight of Ag, 0.1 to 1.0% by weight of Mg, 0.05 to 0.18% by weight of Zr, 0.2 to 0.6% by weight of Mn and at least one element selected from Cr, Sc, Hf and Ti, the quantity of said element, if it is selected, being 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and 0.01 to 0.15% by weight for Ti, the remainder being aluminum and inevitable impurities. The products and methods of the present invention offer a particularly advantageous compromise between static mechanical strength and damage tolerance and are particularly useful in the field of aeronautical design.

Abstract: Wrought product made of aluminum alloy composed as follows, as a percentage by weight Mg: 4.0-5.0; Li: 1.0-1.6; Zr: 0.05-0.15; Ti: 0.01-0.15; Fe: 0.02-0.2; Si: 0.02-0.2; Mn: ?0.5; Cr?0.5; Ag: ?0.5; Cu?0.5; Zn?0.5; Sc?0.01; other elements <0.05; the rest aluminum.

Abstract: The present disclosure relates to an alloy containing aluminum including, as a % by weight, 2.1 to 2.4% of Cu, 1.3 to 1.6% of Li, 0.1 to 0.5% of Ag, 0.2 to 0.6% of Mg, 0.05 to 0.15% of Zr, 0.1 to 0.5% of Mn, 0.01 to 0.12% of Ti, optionally at least one element chosen from among Cr, Sc, and Hf, the quantity of the element, if it is chosen, being from 0.05 to 0.3% for Cr and Sc, 0.05 to 0.5% for Hf, a quantity of Fe and Si each less than or equal to 0.1 and inevitable impurities at a rate of less than or equal to 0.05 each and 0.15 in total. The alloy can be used to produce extruded, rolled and/or forged products particularly suitable for the manufacture of elements for the lower wing skin of aircrafts.

Abstract: The present invention relates to aluminum-lithium alloys in general and, in particular, such products as used in the aircraft industry and the welding of these.

Abstract: The invention relates to a bi-functional extruded structural element, particularly a stringer for aeronautical construction, comprising a base that can be fixed on a surface, and a body, wherein the base comprises a first aluminum-based alloy, and further wherein the body comprises a second heat treatable aluminum-based alloy, having properties that are different from the properties of the first aluminum based alloy.