Abstract: A manufacturing process for obtaining extruded products made from a 6xxx aluminium alloy, wherein the said manufacturing process comprises following steps: a) homogenizing a billet cast from said aluminium alloy; b) heating the said homogenised cast billet; c) extruding the said billet through a die to form at least a solid or hollow extruded product; d) quenching the extruded product down to room temperature; e) optionally stretching the extruded product to obtain a plastic deformation typically between 0.5% and 5%; f) ageing the extruded product without applying on the extruded product any separate post-extrusion solution heat treatment between steps d) and f). characterised in that: i) the heating step b) is a solution heat treatment where: b1) the cast billet is heated to a temperature between Ts-15° C. and Ts, wherein Ts is the solidus temperature of the said aluminium alloy; b2) the billet is cooled until billet mean temperature reaches a value between 400° C. and 480° C.

Abstract: Aluminium alloys suitable for etched and anodized components, in particular aluminum extrusion alloys of the types containing Magnesium and Silicon, which after being extruded to any wide variety of forms for different applications such as house buildings and other building applications is subjected to etching in a conventional alkaline etching bath and subsequent anodizing, wherein the relation between Cu and Zn is controlled to avoid preferential grain etching and the ratio of Cu/Zn is below 1.

Abstract: A method for producing an aluminum wire that has high strength and high conductivity even when reduced in diameter while having excellent elongation and improved in productivity. A method for producing an aluminum wire includes a solution step of subjecting a heat-treatable aluminum alloy material to a solution treatment, a wire-drawing step of subjecting the solution-treated aluminum alloy material to wire-drawing processing, a softening step of subjecting the wire-drawing processed aluminum alloy material to a softening treatment in a short time within 10 seconds, and an aging step of subjecting the softening-treated aluminum alloy material to an aging treatment.

Abstract: An improved aluminum based alloy containing lithium is disclosed. The alloy may be provided as extruded aluminum-copper-lithium products having improved combinations of strength, fracture toughness, corrosion resistance and relatively low density. The extrusion alloy may include from 2.6 to 3.0 weight percent Cu, from 1.4 to 1.75 weight percent Li, from 0.0 to 0.25 weight percent Mn, from 0.10 to 0.45 weight percent Mg, from 0.05 to 0.15 weight percent Zr, from 0.00-0.10 weight percent Ti, from 0.10 weight percent maximum Si, from 0.12 weight percent maximum Fe, from 0.20 weight percent maximum Zn, and the balance Al and incidental impurities. The alloy should also be essentially Ag-free with Ag only being an accidental impurity in levels less than 0.05 weight percent maximum. In certain embodiments, the aluminum-copper-lithium alloys may be provided in the form of extruded products having improved combinations of strength and fracture toughness.

Abstract: A brazing sheet for brazing in an inert-gas atmosphere without using a flux has a core and a filler material clad to one side or both sides of the core. The core has a chemical composition that contains Mg: 0.35-0.8% (mass %; likewise hereinbelow), the remainder being composed of Al and unavoidable impurities. The filler material has a chemical composition that contains Si: 6-13% and Bi: 0.001-0.05% and Mg: limited less than 0.05%, the remainder being composed of Al and unavoidable impurities.

Abstract: Provided herein are anodized quality AA6xxx series aluminum alloy sheets and methods for making anodized quality AA6xxx series aluminum alloy sheets. Also described herein are products prepared from the anodized quality AA6xxx series aluminum alloy sheets. Such products include consumer electronic products, consumer electronic product parts, architectural sheet products, architectural sheet product parts, and automobile body parts.

Abstract: The method for manufacturing an aluminum alloy member includes a forming step to heat an aluminum (Al) alloy containing magnesium (Mg) at 1.6% by mass or more and 2.6% by mass or less, zinc (Zn) at 6.0% by mass or more and 7.0% by mass or less, copper (Cu) or silver (Ag) at 0.5% by mass or less provided that a total amount of copper (Cu) and silver (Ag) is 0.5% by mass or less, titanium (Ti) at 0.01% by mass or more and 0.05% by mass or less, and aluminum (Al) and inevitable impurities as the remainder at 400° C. or higher and 500° C. or lower and to form the aluminum alloy and a cooling step to cool the formed aluminum alloy at a cooling speed of 2° C./sec or more and 30° C./sec or less and preferably 2° C./sec or more and 10° C./sec or less.

Abstract: An impact absorbing member 10 able to secure absorption energy while lightening weight by absorbing the impact load applied in the axial direction by periodic buckling, wherein the impact absorbing member 10 is provided with a main body 20 comprised of metal sheet and having a polygonal shape in cross-section vertical to an axial direction and a center sheet 30 comprised of metal sheet and provided at a hollow part in the main body along the axial direction, the polygonal shape of the main body 20 includes a pair of long side (20a, 20b) facing each other, the center sheet 30 is joined to each of the long sides (20a, 20b) of the polygonal shape of the main body 20, and the sheet thickness t1 (mm) of the main body 20 and the sheet thickness t2 (mm) of the center sheet 30 satisfy 1.3×t1?t2.

Abstract: An impact absorbing member 10 able to secure absorption energy while lightening weight by absorbing the impact load applied in the axial direction by periodic buckling, wherein the impact absorbing member 10 is provided with a main body 20 comprised of metal sheet and having a polygonal shape in cross-section vertical to an axial direction and a center sheet 30 comprised of metal sheet and provided at a hollow part in the main body along the axial direction, the polygonal shape of the main body 20 includes a pair of long side (20a, 20b) facing each other, the center sheet 30 is joined to each of the long sides (20a, 20b) of the polygonal shape of the main body 20, and the sheet thickness t1 (mm) of the main body 20 and the sheet thickness t2 (mm) of the center sheet 30 satisfy 1.3×t1?t2.

Abstract: An aluminum casting alloy has 8.5-9.5 wt. % silicon, 0.5-2.0 wt. % copper (Cu), 0.27-0.53 wt. % magnesium (Mg), wherein the aluminum casting alloy includes copper and magnesium such that 4.7?(Cu+10Mg)?5.8, and other elements, the balance being aluminum. Selected elements may be added to the base composition to give resistance to degradation of tensile properties due to exposure to heat. The thermal treatment of the alloy is calculated based upon wt. % composition to solutionize unwanted phases having a negative impact on properties and may include a three level ramp-up and soak to a final temperature followed by cold water quenching and artificial aging.

Abstract: High strength forged aluminum alloys and methods for producing the same are disclosed. The forged aluminum alloy products may have grains having a high aspect ratio in at least two planes, generally the L-ST and the LT-ST planes. The forged aluminum alloy products may also have a high amount of texture. The forged products may realize increased strength relative to conventionally prepared forged products of comparable product form, composition and temper.

Abstract: A method of manufacturing a formed aluminum alloy structural part or a body-in-white (BIW) part of a motor vehicle. The method includes: providing a rolled aluminum sheet product wherein the aluminum alloy is an AA7000-series aluminum alloy and has a gauge in a range of 0.5-4 mm and is subjected to a solution heat treatment and has been cooled, forming the aluminum alloy sheet to obtain a three-dimensional formed part, heating the three-dimensional formed part to at least one pre-ageing temperature between 50-250° C., and subjecting the formed and pre-aged motor vehicle component to a paint bake cycle.

Abstract: High strength aluminum alloys based on the Al—Zn—Mg—Cu alloy system preferably include high levels of zinc and copper, but modest levels of magnesium, to provide increased tensile strength without sacrificing toughness. Preferred ranges of the elements include by weight, 8.5-10.5% Zn, 1.4-1.85% Mg, 2.25-3.0% Cu and at least one element from the group Zr, V, or Hf not exceeding about 0.5%, the balance substantially aluminum and incidental impurities. In addition, small amounts of scandium (0.05-0.30%) are also preferably employed to prevent recrystallization. During formation of the alloys, homogenization, solution heat treating and artificial aging processes are preferably employed.

Abstract: An aluminum alloy member including a sheet-like aluminum alloy member having ends joined by friction stir welding, and forming an anodic oxidation coating on a weld front surface or a weld back surface, the aluminum alloy member including 0.3 to 1.5 mass % of Mg, 0.2 to 1.2 mass % of Si, 0.5 mass % or less of Cu, and 0.2 mass % or less of Fe, with the balance being Al and unavoidable impurities, Fe-containing second phase particles having a particle size (circle equivalent diameter) of more than 1 ?m, among second phase particles dispersed in a matrix of the aluminum alloy member, having an average particle size of 5 ?m or less.

Abstract: A method of forming a wrought material having a refined grain structure is provided. The method comprises providing a metal alloy material having a depressed solidus temperature and a low temperature eutectic phase transformation. The metal alloy material is molded and rapidly solidified to form a fine grain precursor that has fine grains surrounded by a eutectic phase with fine dendritic arm spacing. The fine grain precursor is plastic deformed at a high strain rate to cause recrystallization without substantial shear banding to form a fine grain structural wrought form. The wrought form is then thermally treated to precipitate the eutectic phase into nanometer sized dispersoids within the fine grains and grain boundaries and to define a thermally treated fine grain structure wrought form having grains finer than the fine grains and the fine dendritic arm spacing of the fine grain precursor.

Abstract: A casted ingot of a heat treatment type Al—Zn—Mg series aluminum alloy comprising Zn: 4.0-8.0% by mass, Mg: 0.5-2.0% by mass, Cu: 0.05-0.5% by mass, Ti: 0.01-0.1% by mass, and any one or more of Mn: 0.1-0.7% by mass, Cr: 0.1-0.5% by mass and Zr: 0.05-0.3% by mass, and the balance being aluminum and incidental impurities is extruded at a homogenization treatment temperature after a homogenization treatment without cooled, and a resulted extruded material is die quenched at a cooling rate equal to or more than 100° C./min and then subjected to an artificial aging treatment, wherein the homogenization treatment is carried out by heating to the homogenization treatment temperature as 430-500° C. at a heating rate less than 750° C./hr or by heating to the homogenization treatment temperature and held the homogenization treatment temperature for 3 hours.

Abstract: An Al—Mg—Si-based high-strength aluminum alloy extruded shape exhibits excellent corrosion resistance and ductility, and exhibits excellent hardenability during extrusion (i.e., ensures high productivity). A method for producing the same is also disclosed. The high-strength aluminum alloy extruded shape includes 0.65 to 0.90 mass % of Mg, 0.60 to 0.90 mass % of Si, 0.20 to 0.40 mass % of Cu, 0.20 to 0.40 mass % of Fe, 0.10 to 0.20 mass % of Mn, and 0.005 to 0.1 mass % of Ti, with the balance being Al and unavoidable impurities, the aluminum alloy extruded shape having a stoichiometric Mg2Si content of 1.0 to 1.3 mass %, an excess Si content relative to stoichiometric Mg2Si of 0.10 to 0.30 mass %, and a total content of Fe and Mn of 0.35 mass % or more.

Abstract: A high-strength aluminum material having a chemical composition which includes Zn: more than 7.2% (mass %, the same applies hereafter) and 8.7% or less, Mg: 1.3% or more and 2.1% or less, Cu: less than 0.50%, Fe: 0.30% or less, Si: 0.30% or less, Mn: less than 0.05%, Cr: 0.20% or less; Zr: less than 0.05%, Ti: 0.001% or more and 0.05% or less, the balance being Al and unavoidable impurities, is provided. It has a proof stress of 350 MPa or more, and a metallographic structure formed of a recrystallized structure. The recrystallized structure is comprised of crystal grains having an average particle diameter of 500 ?m or less, and a crystal grain length in a direction parallel to a hot working direction is 0.5 to 4 times as long as a crystal grain length in a direction perpendicular to the hot working direction.

Abstract: High strength forged aluminum alloys and methods for producing the same are disclosed. The forged aluminum alloy products may have grains having a high aspect ratio in at least two planes, generally the L-ST and the LT-ST planes. The forged aluminum alloy products may also have a high amount of texture. The forged products may realize increased strength relative to conventionally prepared forged products of comparable product form, composition and temper.

Abstract: A high-strength aluminum alloy extruded material contains Si: 0.70 to 1.3 mass %; Mg: 0.45 to 1.2 mass %; Cu: 0.15 to less than 0.40 mass %; Mn: 0.10 to 0.40 mass %; Cr: more than 0 to 0.06 mass %; Zr: 0.05 to 0.20 mass %; Ti: 0.005 to 0.15 mass %, Fe: 0.30 mass % or less; V: 0.01 mass % or less; the balance being Al and unavoidable impurities Crystallized products in the alloy have a particle diameter of a is 5 ?m or less. Furthermore, an area ratio of a fibrous structure in a cross section parallel to an extruding direction during hot extrusion is 95% or more.

Abstract: An aluminum alloy material exhibiting excellent bendability can be produced without performing a straightening step, and can be bent without developing orange peel. The aluminum alloy material is a T4-tempered material formed of an Al—Cu—Mg—Si alloy including 1.0 to 2.5 mass % of Cu, 0.5 to 1.5 mass% of Mg, and 0.5 to 1.5 mass % of Si, with the balance being aluminum and unavoidable impurities, a matrix that forms an inner part of the aluminum alloy material having a microstructure formed by recrystallized grains having an average crystal grain size of 200 ?m or less, and the aluminum alloy material having a ratio “tensile strength/yield strength” determined by a tensile test of 1.5 or more.

Abstract: Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The invention alloy is useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction. The invention alloy may be aged by 2 or 3 step practices while exceeding the SCC requirements for applications for which the invention alloy is primarily intended.

Abstract: An aluminum alloy includes, in weight percent, 0.70-0.85 Si, 0.14-0.25 Fe, 0.25-0.35 Cu, 0.05 max Mn, 0.75-0.90 Mg, 0.12-0.18 Cr, 0.05 max Zn, and 0.04 max Ti, the balance being aluminum and unavoidable impurities. The alloy may be suitable for extruding, and may be formed into an extruded alloy product.

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: The present invention provides a high-strength aluminum alloy extruded product exhibiting excellent corrosion resistance and secondary workability and suitably used as a structural material for transportation equipment such as automobiles, railroad vehicles, and aircrafts, and a method of manufacturing the same. The aluminum alloy extruded product has a composition containing 0.6 to 1.2% of Si, 0.8 to 1.3% of Mg, and 1.3 to 2.1% of Cu while satisfying the following conditional expressions (1), (2), (3) and (4), 3%?Si %+Mg %+Cu %?4%??(1) Mg %?1.7×Si %??(2) Mg %+Si %?2.7%??(3) Cu %/2?Mg %?(Cu %/2)+0.6%??(4) and further containing 0.04 to 0.35% of Cr, and 0.05% or less of Mn as an impurity, with the balance being aluminum and unavoidable impurities. The cross section of the extruded product has a recrystallized structure with an average grain size of 500 ?m or less.

Abstract: A casted ingot of a heat treatment type Al—Zn—Mg series aluminum alloy comprising Zn: 4.0-8.0% by mass, Mg: 0.5-2.0% by mass, Cu: 0.05-0.5% by mass, Ti: 0.01-0.1% by mass, and any one or more of Mn: 0.1-0.7% by mass, Cr: 0.1-0.5% by mass and Zr: 0.05-0.3% by mass, and the balance being aluminum and incidental impurities is extruded at a homogenization treatment temperature after a homogenization treatment without cooled, and a resulted extruded material is die quenched at a cooling rate equal to or more than 100° C./min and then subjected to an artificial aging treatment, wherein the homogenization treatment is carried out by heating to the homogenization treatment temperature as 430-500° C. at a heating rate less than 750° C./hr or by heating to the homogenization treatment temperature and held the homogenization treatment temperature for 3 hours.

Abstract: A population of extrusion billets has a specification such that every billet is of an alloy of composition (in wt. %): Fe<0.35; Si 0.20-0.6; Mn<0.10; Mg 0.25-0.9; Cu<0.015; Ti<0.10; Cr<0.10; Zn<0.03; balance Al of commercial purity. After ageing to T5 or T6 temper, extruded sections can be etched and anodised to give extruded matt anodised sections having improved properties.

Abstract: Disclosed is an Al—Mg—Si aluminum alloy extrudate which contains, in terms of mass %, 0.60-1.20% Mg, 0.30-0.95% Si, 0.01-0.40% Fe, 0.30-0.52% Mn, 0.001-0.65% Cu, and 0.001-0.10% Ti and in which the contents of Mg and Si satisfy Mg(%)?(1.73×Si(%)?0.25)?0 and the remainder comprises Al. The extrudate has an equi-axed recrystallized grain texture in which the areal proportion of recrystallized grains is 65% or higher. In examination with a TEM having a magnification of 5,000, intergranular precipitate grains having a size of 1 ?m or more in terms of center-of-gravity diameter are apart from one another at an average spacing exceeding 25 ?m. The average areal proportion of Goss-orientation grains is less than 8% throughout the whole thickness of this extrudate.

Abstract: A method includes: preparing a molten aluminum alloy consisting of 0.3-0.8 mass % Mg, 0.5-1.2 mass % Si, 0.3 mass % or more excess Si relative to the Mg2Si stoichiometric composition, 0.05-0.4 mass % Cu, 0.2-0.4 mass % Mn, 0.1-0.3 mass % Cr, 0.2 mass % or less Fe, 0.2 mass % or less Zr, and 0.005-0.1 mass % Ti, with the balance being aluminum and unavoidable impurities; casting the alloy into a billet at a speed of 80 mm/min or more and a cooling rate of 15° C./sec or more; extruding the billet into an extruded product; water cooling the product immediately after extrusion at 500° C./min or more; and artificially aging the product, thereby yielding an extruded product with fatigue strength of 140 MPa or more, fatigue ratio of 0.45 or more, an interval between striations on a fatigue fracture surface of 5.0 ?m or less, and a maximum length of Al—Fe—Si crystallized products of 10 ?m or less.

Abstract: An aluminum alloy extruded product includes an aluminum alloy including 6.0 to 7.2 mass % of Zn, 1.0 to 1.6 mass % of Mg, 0.1 to 0.4 mass % of Cu, at least one component selected from the group consisting of Mn, Cr, and Zr in a respective amount of 0.25 mass % or less and a total amount of 0.15 to 0.25 mass %, 0.20 mass % or less of Fe, and 0.10 mass % or less of Si, with the balance substantially being aluminum, the aluminum alloy extruded product having a hollow cross-sectional shape, a recrystallization rate of 20% or less of a cross-sectional area of the extruded product, and a 0.2% proof stress of 370 to 450 MPa.

Abstract: An extruded member of Al—M13 Si aluminum alloy specially composed of Mg, Si, Fe, Cu, Zn, Ti, etc. which has the equiaxed re-crystallized grain structure in which intergranular precipitates 1 ?m or larger are separate from one another at large average intervals and there are many cube orientations over the entire thickness region thereof so that it excels in both flexural crushing performance and corrosion resistance. The extruded member is suitable for use as automotive body reinforcement members which need outstanding lateral crushing performance under severe collision conditions as well as good corrosion resistance.

Abstract: 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<0.15; Si<0.15; Zr?0.05; Ag<0.01, other elements <0.05 each and <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.

Abstract: The present invention provides a high-strength aluminum alloy extruded product exhibiting excellent corrosion resistance and secondary workability and suitably used as a structural material for transportation equipment such as automobiles, railroad vehicles, and aircrafts, and a method of manufacturing the same. The aluminum alloy extruded product has a composition containing 0.6 to 1.2% of Si, 0.8 to 1.3% of Mg, and 1.3 to 2.1% of Cu while satisfying the following conditional expressions (1), (2), (3) and (4), 3%?Si %+Mg %+Cu %?4%??(1) Mg %?1.7×Si %??(2) Mg %+Si %?2.7%??(3) Cu %/2?Mg %?(Cu %/2)+0.6%??(4) and further containing 0.04 to 0.35% of Cr, and 0.05% or less of Mn as an impurity, with the balance being aluminum and unavoidable impurities. The cross section of the extruded product has a recrystallized structure with an average grain size of 500 ?m or less.

Abstract: The invention concerns a method for producing a substance during which an aluminum base alloy is produced that has a content of 5.5 to 13.0% by mass of silicon and a content of magnesium according to formula Mg [% by mass]=1.73×Si [% by mass]+m with m=1.5 to 6.0% by mass of magnesium, and has a copper content ranging from 1.0 to 4.0% by mass. The base alloy is then subjected to at least one hot working and, afterwards, to a heat treatment consisting of solution annealing, quenching and artificial aging. The magnesium is added based on the respectively desired silicon content according to the aforementioned formula. The material obtained by using the inventive method comprises having a low density and a high strength.

Abstract: High temperature heat treatable aluminum alloys that can be used at temperatures from about ?420° F. (?251° C.) up to about 650° F. (343° C.) are described. The alloys are strengthened by dispersion of particles based on the L12 intermetallic compound Al3X. These alloys comprise aluminum, magnesium, lithium, at least one of scandium, erbium, thulium, ytterbium, and lutetium, and at least one of gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.

Abstract: A method of producing bicycle ratchet bushing is provided, wherein an alloyed fundamental material is applied to the processes of a modeling process and a detailing treatment to form a product of bicycle ratchet bushing. Wherein, when the processes of drilling and tapping a hole of the modeling process are completed, the tapped hole of the workpiece is connected to a screw rod, and the screw rod is clamped by a drawing machine, so that the workpiece can be penetrated through the mold of the drawing machine to proceed with the drawing process. When the drawing process is working, it is not necessary to apply a head-hitting process to the workpiece as the conventional drawing method does, therefore the outer teeth of the ratchet of the workpiece will not be deformed by an external force, and can penetrated into the mold for further drawing process, therefore the whole manufacturing processes can be controlled efficiently.

Abstract: A first step of performing solution treatment to a pipe material of a precipitation-hardening type aluminum alloy of high hardness extruded, a second step of performing spinning work to the solution-treated pipe material, and a third step of performing artificial aging to the spinning-worked pipe material.

Abstract: A heat-treated high-strength Al—Cu—Mg—Si aluminum alloy product exhibits excellent extrudability and high strength. The high-strength Al—Cu—Mg—Si aluminum alloy product obtained by extrusion is characterized in that the microstructure of the entire surface of the cross section of the aluminum alloy product is formed of recrystallized grains, the grains have an average aspect ratio (L/t) of 5.0 or less (wherein L is the average size of the grains in the extrusion direction, and t is the average thickness of the grains), and the orientation density of the grains in the microstructure, for which the normal direction to the {001} plane is parallel to the extrusion direction in comparison with the grains orientated to random orientations, is 50 or less.

Abstract: Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The instantly disclosed alloys are useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction.

Abstract: A method for producing an integrated monolithic aluminum structure, including the steps of: (a) providing an aluminum alloy plate from an aluminum alloy with a predetermined thickness (y), (b) shaping or forming the alloy plate to obtain a predetermined shaped structure, (c) heat-treating the shaped structure, (d) machining, e.g. high velocity machining, the shaped structure to obtain an integrated monolithic aluminum structure.

Abstract: High temperature heat treatable aluminum alloys that can be used at temperatures from about ?420° F. (?251° C.) up to about 650° F. (343° C.) are described. The alloys are strengthened by dispersion of particles based on the L12 intermetallic compound Al3X. These alloys comprise aluminum, magnesium, lithium, at least one of scandium, erbium, thulium, ytterbium, and lutetium, and at least one of gadolinium, yttrium, zirconium, titanium, hafnium, and niobium.

Abstract: An extruded member of Al—Mg—Si aluminum alloy specially composed of Mg, Si, Fe, Cu, Zn, Ti, etc. which has the equiaxed re-crystallized grain structure in which intergranular precipitates 1 ?m or lager are separate from one another at large average intervals and there are many cube orientations over the entire thickness region thereof so that it excels in both flexural crushing performance and corrosion resistance. The extruded member is suitable for use as automotive body reinforcement members which need outstanding lateral crushing performance under severe collision conditions as well as good corrosion resistance.

Abstract: A method for producing a heat treated aluminum alloy product in a shortened period of time, the method comprising: (a) providing a heat treatable aluminum alloy; (b) working the heat treatable aluminum alloy at a solutionizing temperature to form a product; (c) first stage cooling the product to a critical temperature at which precipitation of second phase particles of the heat treatable aluminum alloy is negligible, wherein the first stage cooling comprises a first stage cooling rate from about 15° F. per second to about 100° F. per second; (d) second stage cooling the product to ambient temperature; (e) heating the product to an artificial aging temperature; and (f) artificially aging the product at the artificial aging temperature for a predetermined artificial aging time to form the heat treated aluminum alloy product.

Abstract: This invention relates to a 6000-series aluminum extruded material containing magnesium (0.3% to 0.7% by mass), silicon (0.7% to 1.5% by mass), copper (0.35% or less by mass), iron (0.35% or less by mass), titanium (0.005% to 0.1% by mass), manganese (0.05% to 0.30% by mass), chrome (0.10% or less by mass), and zirconium (0.10% or less by mass) (provided that at least one transition element selected from the group consisting of manganese, chromium, and zirconium is contained in a total amount representing 0.05% to 0.40% by mass), with the balance comprising aluminum with inevitable impurities, such aluminium extruded material having a predetermined yield strength of 180 MPa or more with an increase of 60 MPa as a result of a thermal history corresponding to paint baking.

Abstract: Disclosed is a method of heat treating an aluminum alloy member having a main surface, including the steps of (a) subjecting the member to a solution heat treatment (b) quenching the member and (c) reheating the member in a pre-ageing heat treatment step. The pre-ageing heat treatment is conducted by holding the aluminum alloy member close to a heating plate. Also disclosed is a product produced according to this method, and to an apparatus for performing the pre-ageing heat treatment.

Abstract: Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The invention alloy is useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction. The invention alloy may be aged by 2 or 3 step practices while exceeding the SCC requirements for applications for which the invention alloy is primarily intended.

Abstract: The present invention relates to an extruded, rolled and/or forged product made of an aluminum alloy. Alloys of the present invention may comprise (by mass): Zn 6.7-7.5% Cu 2.0-2.8% Mg 1.6-2.2% at least one element selected from the group composed of: i Zr 0.08-0.20% Cr 0.05-0.25% Sc 0.01-0.50% Hf 0.05-0.20% and V 0.02-0.20% Fe+Si<0.20% other elements ?0.05 each and ?0.15 total, balance aluminum. Products of the present invention in some embodiments have an improved compromise between static mechanical strength and damage tolerance.

Abstract: A method of press quenching a 6020 aluminum alloy comprising the steps of providing an ingot or billet of 6020 aluminum alloy consisting essentially of about 0.5 to about 0.6% silicon, about 0.7 to about 0.8% magnesium, about 0.55 to about 0.65% copper, about 0.35 to about 0.45% iron, about 0.01 to about 0.04% manganese, about 1.05 to about 1.15% tin, and about 0.04 to about 0.06% chromium; homogenizing the billet, cooling the billet, reheating the billet, extruding the billet, quenching the extrusion, and artificially aging the extrusion. The alloy has enhanced productivity, strength, and machinability and can be used as a direct replacement for lead containing alloy 6262 T-6.

Abstract: The high-purity aluminum sputter target is at least 99.999 weight percent aluminum and has a grain structure. The grain structure is at least 99 percent recrystallized and has a grain size of less than 200 ?m. The method forms high-purity aluminum sputter targets by first cooling a high-purity target blank to a temperature of less than ?50 ° C. and then deforming the cooled high-purity target blank introduces intense strain into the high-purity target. After deforming, recrystallizing the grains at a temperature below 200 ° C. forms a target blank having at least 99 percent recrystallized grains. Finally, finishing at a low temperature sufficient to maintain the fine grain size of the high-purity target blank forms a finished sputter target.

Abstract: 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<0.15; Si<0.15; Zr?0.05; Ag<0.01, other elements <0.05 each and <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.