Abstract: The invention relates to a method for producing a wrought product made of an aluminum alloy composed, in wt %, of Mg: 3.8-4.2; Mn: 0.3-0.8 and preferably 0.5-0.7; Sc: 0.1-0.3; Zn: 0.1-0.4; Ti: 0.01-0.05; Zr: 0.07-0.15; Cr: <0.01; Fe: <0.15; Si<0.1; wherein the homogenization is carried out at a temperature of between 370° C. and 450° C., for between 2 and 50 hours, such that the equivalent time at 400° C. is between 5 and 100 hours, and the hot deformation is carried out at an initial temperature of between 350° C. and 450° C. The invention also relates to hot-worked products obtained by the method according to the invention, in particular sheets with a thickness of less than 12 mm. The products according to the invention are advantageous as they offer a better compromise in terms of mechanical strength, toughness and hot-formability.

Abstract: Extrados structural element made from an aluminum, copper and lithium alloy and method for manufacturing same. An alloy with composition (in wt %) 4.2-5.2 Cu, 0.9-1.2 Li, 0.1-0.3 Ag, 0.1-0.25 Mg, 0.08-0.18 Zr, 0.01-0.15 Ti, an Fe and Si content level less than or equal to 0.1% each, and other element with content level less than or equal to 0.05% each and 0.15% in total, is poured, homogenized, deformed hot, placed in a solution at a temperature of at least 515° C., pulled from 0.5 to 5% and annealed. The combination of magnesium, copper and manganese content with the temperature in solution can reach an advantageous elasticity under compression limit. Products having a thickness of at least 12 mm have, in the longitudinal direction, an elasticity under compression limit of at least 645 MPa and an elongation of at least 7%.

Abstract: The disclosure relates to a needle cover for protecting a needle mounted on a tip of a medical injection device. The tip comprises a distal bulge. The needle cover comprises an inner needle shield made of a material with elastomeric properties. The inner needle shield comprises an inner sealing portion configured to sealingly contact the outer surface of the bulge, wherein the inner sealing portion comprises one or more ribs extending inwardly along the circumference of the inner sealing portion. At least one rib is a continuous rib in the form of a ring configured to provide a continuous contact with the outer surface of the bulge.

Abstract: The invention relates to a product based on an aluminium alloy comprising, as percentages by weight, 4.0 to 4.6% by weight of Cu, 0.7 to 1.2% by weight of Li, 0.5 to 0.65% by weight of Mg, 0.10 to 0.20% by weight of Zr, 0.15 to 0.30% by weight of Ag, 0.25 to 0.45% by weight of Zn, 0.05 to 0.35% by weight of Mn, at most 0.20% by weight of Fe+Si, at least one element selected from Cr, Sc, Hf, V and Ti, the amount of said element, if selected, being from 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and for V and 0.01 to 0.15% by weight for Ti, the other elements being at most 0.05% by weight each and 0.15% by weight in total, the remainder being aluminium. The invention also relates to a method for obtaining such a product and to the use thereof as an aircraft structural element.

Abstract: The invention relates to a manufacturing method in which an alloy is prepared that comprises 3.5 to 4.7 wt % of Cu; 0.6 to 1.2 wt % of Li; 0.2 to 0.8 wt % of Mg; 0.1 to 0.2 wt % of Zr; 0.0 to 0.3 wt % of Ag; 0.0 to 0.8 wt % of Zn; 0.0 to 0.5 wt % of Mn; at most 0.20 wt % of Fe+Si; optionally an element selected from Cr, Sc, Hf and V, the amount of said element, if selected, being from 0.05 to 0.3 wt % for Cr and for Sc, 0.05 to 0.5 wt % for Hf and for V; the other elements being at most 0.05 wt % each and 0.15 wt % in total, a refiner is introduced, the alloy is cast in a crude form, homogenized, hot-worked, solution heat-treated, quenched, cold-worked, and tempered, in which the refiner contains particles of TiC and/or the cold working is between 8 and 16%. The products obtained by the method according to the invention have an advantageous compromise between mechanical strength and toughness.

Abstract: The invention relates to a method for producing a wrought product made of an aluminum alloy composed, in wt %, of Mg: 3.8-4.2; Mn: 0.3-0.8 and preferably 0.5-0.7; Sc: 0.1-0.3; Zn: 0.1-0.4; Ti: 0.01-0.05; Zr: 0.07-0.15; Cr: <0.01; Fe: <0.15; Si<0.1; wherein the homogenization is carried out at a temperature of between 370° C. and 450° C., for between 2 and 50 hours, such that the equivalent time at 400° C. is between 5 and 100 hours, and the hot deformation is carried out at an initial temperature of between 350° C. and 450° C. The invention also relates to hot-worked products obtained by the method according to the invention, in particular sheets with a thickness of less than 12 mm. The products according to the invention are advantageous as they offer a better compromise in terms of mechanical strength, toughness and hot-formability.

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 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 wrought aluminum and magnesium alloy products (type Al—Mg, also known under the name of aluminum alloy of the 5XXX series according to the Aluminum Association), more particularly Al—Mg—Zr alloy products having a high mechanical strength and good aptitude for forming. The invention also has for object a method for manufacturing as well as the use of these products intended for transports and in particular in aeronautics and space construction.

Abstract: The invention relates to an extruded product made from an alloy of composition (% by weight): Cu: 5.05-5.35 Mg: 0.20-0.40 Mn: 0.20-0.40 Zr: 0.08-0.15 Ti: 0.01-0.15 Zn: 0-0.15 Si<0.10 Fe<0.15 and other elements<0.05 each and <0.15 in total, the remainder being Al, treated by solution heat treatment, at a temperature between 525 and 540° C., quenching, controlled stretching during quenching until a permanent set of at least 1.5% is achieved, and ageing at a temperature of between 160 and 190° C. The products according to the invention are particularly well suited to use as pistons in an internal combustion engine of a vehicle and, in particular, of a racing car.

Abstract: An extruded product made of an alloy containing aluminum comprising 4.2 wt % to 4.8 wt % of Cu, 0.9 wt % to 1.1 wt % of Li, 0.15 wt % to 0.25 wt % of Ag, 0.2 wt % to 0.6 wt % of Mg, 0.07 wt % to 0.15 wt % of Zr, 0.2 wt % to 0.6 wt % of Mn, 0.01 wt % to 0.15 wt % of Ti, a quantity of Zn less than 0.2 wt %, a quantity of Fe and Si less than or equal to 0.1 wt % each, and unavoidable impurities with a content less than or equal to 0.05 wt % each and 0.15 wt % in total is disclosed. The profiles according to the invention are particularly useful as fuselage stiffeners or stringers, circumferential frames, wing stiffeners, floor beams or profiles, or seat tracks, notably owing to their improved properties in relation to those of known products, in particular in terms of energy absorption during an impact, static mechanical strength and corrosion resistance properties and their low density.

Abstract: The disclosure provides for wrought products made of Al—Cu—Mg aluminum alloy composed as follows, as a percentage by weight, Cucorr: 2,6-3.7; Mgcorr: 1.5-2.6, Mn: 0.2-0.5; Zr: ?0.16; Ti: 0.01-0.15; Cr?0.25; Si?0.2; Fe?0.2; other elements <0.05 the rest aluminum; with Cucorr>?0.9(Mgcorr)+4.3 and Cucorr<?0.9(Mgcorr)+5.0; where Cucorr=Cu?0.74(Mn?0.2)?2.28 Fe and Mgcorr=Mg?1.73(Si?0.05) for Si?0.05 and Mgcorr=Mg for Si<0.05 and their manufacturing process.

Abstract: The invention relates to a wrought product made of an aluminum alloy having the composition in % by weight, Mg: 4.0-5.0; Li: 1.0-1.8; Mn: 0.3-0.5; Zr: 0.05-0.15; Ag: ?0.5; Fe: ?0.1; Ti: <0.15; Si: ?0.05; other elements ?0.05 each and ?0.15 in association; the remainder is aluminum. The invention further relates to a method for manufacturing a wrought product wherein an unprocessed form of aluminum alloy is cast, which has the composition, in % by weight: Mg: 4.0-5.0; Li: 1.0-1.8; Mn: 0.3-0.5; Zr: 0.05-0.15; Ag: ?0.5; Fe: ?0.1; Ti: <0.15; Si: ?0.05; other elements ?0.05 each and ?0.15 in combination; the remainder is aluminum; optionally, said unprocessed form is homogenized; said unprocessed form is hot worked to obtain a hot-worked product; optionally, said hot-worked product is solution heat treated at a temperature from 360° C. to 460° C., preferably from 380° C. to 420° C.

Abstract: The invention relates to a method for manufacturing a wrought product. The invention further provides, a wrought product able to be obtained according to the method of the invention as well as the use of said wrought product to produce aircraft structural elements.

Abstract: The invention relates in particular to an unprocessed extruded product for manufacturing a machined extruded product for the aeronautical industry, made of an Al—Cu—Li alloy. The invention also relates to the method for manufacturing a machined extruded product and to the corresponding machined extruded product. The products according to the invention are useful in particular for manufacturing floor beams and girders.

Abstract: The invention relates to an extrados structural element made from an aluminum, copper and lithium alloy and a method for manufacturing same. In the method according to the invention, an alloy with composition (in wt %) 4.2 to 5.2 Cu, 0.9 to 1.2 Li, 0.1 to 0.3 Ag, 0.1 to 0.25 Mg, 0.08 to 0.18 Zr, 0.01 to 0.15 Ti, optionally up to 0.2 Zn, optionally up to 0.6 Mn, an Fe and Si content level less than or equal to 0.1% each, and other element with a content level less than or equal to 0.05% each and 0.15% in total, the aluminum is poured, homogenized, deformed hot and optionally cold, placed in a solution at a temperature of at least 515° C., pulled from 0.5 to 5% and annealed. The combination in particular of the magnesium, copper and manganese content with the temperature in solution can reach a very advantageous elasticity under compression limit.

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 an extruded product made of an alloy containing aluminum comprising 4.2 wt % to 4.8 wt % of Cu, 0.9 wt % to 1.1 wt % of Li, 0.15 wt % to 0.25 wt % of Ag, 0.2 wt % to 0.6 wt % of Mg, 0.07 wt % to 0.15 wt % of Zr, 0.2 wt % to 0.6 wt % of Mn, 0.01 wt % to 0.15 wt % of Ti, a quantity of Zn less than 0.2 wt %, a quantity of Fe and Si less than or equal to 0.1 wt % each, and unavoidable impurities with a content less than or equal to 0.05 wt % each and 0.15 wt % in total. The profiles according to the invention are particularly useful as fuselage stiffeners or stringers, circumferential frames, wing stiffeners, floor beams or profiles, or seat tracks, notably owing to their improved properties in relation to those of known products, in particular in terms of energy absorption during an impact, static mechanical strength and corrosion resistance properties and their low density.

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.