Abstract: The invention relates to a fabrication process to obtain aluminum alloy sheet having high formability. In this process, an alloy obtained by alloying Al with Si, Mg, Cu, Mn and Fe, and one or more elements taken from the group of Cr, Zn, Zr and Ti, is subjected to a continuous solution treatment for at least 3 seconds at a temperature higher than 450.degree. C., followed by cooling to a temperature between 60.degree. and 250.degree. C., at a rate higher than 100.degree. C./min, followed by a coiling at the same temperature in the 60.degree. C.-250.degree. C. range and a preaging between 1 minute and 10 hours at the same cooling temperature of 60.degree. to 250.degree. C.

Abstract: An improvement to a process for treating an aluminum alloy for the series AA 2000 or AA 6000 comprising solution heat treating, quenching and natural or artificial aging, in which conventional heat solution heat treating is defined as solution heat treating the alloy at a temperature which is 5.degree. to 10.degree. C. below a known eutectics melting temperature for the alloy. The improvement comprises solution heat treating at a temperature which is 10.degree. to 100.degree. C. below the conventional solution heat treating temperature in order to desensitize the alloy to intercrystalline corrosion.

Abstract: An alloy of aluminum containing magnesium, silicon and optionally copper in amounts in percent by weight falling within one of the following ranges:(1) 0.4.ltoreq.Mg.ltoreq.0.8, 0.2.ltoreq.Si.ltoreq.0.5, 0.3.ltoreq.Cu.ltoreq.3.5;(2) 0.8.ltoreq.Mg.ltoreq.1.4, 0.2.ltoreq.Si.ltoreq.0.5, Cu.ltoreq.2.5; and(3) 0.4.ltoreq.Mg.ltoreq.1.0, 0.2.ltoreq.Si.ltoreq.1.4, Cu.ltoreq.2.0; said alloyhaving been formed into a sheet having properties suitable for automotive applications. The alloy may also contain at least one additional element selected from the group consisting of Fe in an amount of 0.4 percent by weight or less, Mn in an amount of 0.4 percent by weight or less, Zn in an amount of 0.3 percent by weight or less and a small amount of at least one other element, such as Cr, Ti, Zr and V.

Abstract: AA 7000 series alloys having high mechanical strength and a process for obtaining them. The alloys contain, by weight, 7 to 13.5% Zn, 1 to 3.8% Mg, 0.6 to 2.7% Cu, 0 to 0.5% Mn, 0 to 0.4% Cr, 0 to 0.2% Zr, others up to 0.05% each and 0.15% total, and remainder Al. Either wrought or cast alloys can be obtained, and the specific energy associated with the DEA melting signal of the product is lower than 3 J/g.

Abstract: An improved high strength aluminum alloy product having good combinations of strength, toughness, corrosion resistance and the ability to be subjected in sheet or strip form to roll forming or shaping operations to produce elongate stringer or other aerospace structural reinforcing members. The alloy consists essentially of about 7.6 to 8.4% zinc, about 1.8 to 2.2% magnesium, about 2 to 2.6% copper and at least one element selected from zirconium, vanadium and hafnium present in a total amount not exceeding about 0.5%, preferably about 0.05 to 0.25% zirconium, the balance aluminum and incidental elements and impurities. The improved strip is preferably produced by homogenizing, hot rolling and thermally treating or annealing at about 750.degree. to 850.degree. F., preferably around 800.degree. F.

Abstract: A method is disclosed for the production of aluminum-copper-lithium alloys that exhibit improved strength and fracture toughness at cryogenic temperatures. Improved cryogenic properties are achieved by controlling the composition of the alloy, along with processing parameters such as the amount of cold-work and artificial aging. The ability to attain substantially equal or greater strength and fracture toughness at cryogenic temperature in comparison to room temperature allows for use of the alloys in cryogenic tanks for space launch vehicles and the like.

Abstract: The mechanical properties of aluminium alloy extrusion in a specified transverse direction are improved by upsetting the extrusion billet in at least one direction chosen with reference to the specified transverse direction. For example, the extrusion billet may be of generally circular cross-section with one or two opposite segments arising. The extrusion may be subjected to thermomechanical treatment and/or vibration treatment. A preferred final thermomechanical treatment is also described.

Abstract: Strength and ductility for a aluminum-lithium alloy wrought product in the transverse direction is improved by subjecting these types of alloys to improved T8 temper practice. The wrought product, after solution heat treating and quenching is subjected to a multiple step stretching sequence prior to aging, the total percent reduction for the multiple step stretching sequence ranging between 1 and 20 percent reduction. In the multiple step stretching sequence, each of the stretching steps may have the same or different amounts of percent reduction to achieve the desired total percent reduction. An aluminum-lithium alloy wrought product subjected to the improved T8 temper practice has increased tensile yield stress and percent elongation in its transverse direction to facilitate commercial application of the product in high strength applications.

Abstract: A method of producing an aluminum-based alloy product having improved exfoliation resistance and fracture toughness which comprises providing an aluminum-based alloy composition consisting essentially of about 5.5-10.0% by weight of zinc, about 1.75-2.6% by weight of magnesium, about 1.8-2.75% by weight of copper with the balance aluminum and other elements. The aluminum-based alloy is worked, heat treated, quenched and aged to produce a product having improved corrosion resistance and mechanical properties. The amounts of zinc, magnesium and copper are stoichiometrically balanced such that after precipitation is essentially complete as a result of the aging process, no excess elements are present. The method of producing the aluminum-based alloy product utilizes either a one- or two-step aging process in conjunction with the stoichiometrically balancing of copper, magnesium and zinc.

Abstract: A method for heat treating an aluminum part is provided. The method includes heat treating the aluminum alloy part with direct radiation from a source of infrared energy until the part attains a desired state of heat treatment. The method and apparatus further include monitoring of the part and controlling the intensity of the radiation source through proportional control in response to the measured temperature.

Abstract: Disclosed is a method of producing a forged and rolled Al-Zn-Cu-Mg alloy plate product having improved fatigue properties in the long transverse direction. The method comprises providing a body of an Al-Zn-Cu-Mg alloy, working said body by a forging operation to reduce its thickness in a C direction by at least 30% and rolling or working the forged body to provide a forged and rolled plate product having improved fatigue properties in the long transverse direction.

Abstract: The present invention provides a method for improving aluminum alloy plate product properties by delaying final stretching of the plate product. During processing of the product, a time interval or intentional delay is provided between the final cold rolling step and the final stretching step. By delaying the final stretching procedure, an aluminum alloy plate product is provided with an improved fracture toughness without significant decrease in strength values. The method of intentionally delaying final stretching is particularly adapted for 2000 series aluminum alloys.

Abstract: An alloy product having improved combinations of strength, density, toughness and corrosion resistance, said alloy product consisting essentially of about 7.6 to 8.4% zinc, about 1.8 to 2.2% magnesium, about 2 to 2.6% copper and at least one element selected from zirconium, vanadium and hafnium present in a total amount not exceeding about 0.5%, preferably about 0.05 to 0.25% zirconium, the balance aluminum and incidential elements and impurities. The alloy product, suitable for aerospace applications, exhibits high yield strength, at least about 10% greater yield strength than its 7X50-T6 counterpart, with good toughness and corrosion resistance properties typically comparable to or better than those of its 7X50-T76 counterpart. Upper wing members made from this alloy typically have a yield strength over 84 ksi, good fracture toughness and an EXCO exfoliation resistance level of "EC" or better, typically "EB".