Abstract: This invention relates to a method for artificially aging 7000 Series Al aerospace alloys to impart improved strength and/or corrosion resistance performance thereto. The method purposefully adds a second aging step or stage to a one-step tempering, or a third step/stage to a low-high, two-step aging operation. The added step/stage extends at about 225-275° F. for about 3-24 hours. More preferably, the added stage extends at about 250° F. for about 6 hours or more.

Abstract: Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg?(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the three stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

Abstract: Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg?(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the three stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

Abstract: A substantially unrecrystallized extrusion comprising about 3.6 to about 4.2 wt. % copper, about 1.0 to about 1.6 wt. % magnesium, about 0.3 to about 0.8 wt. % manganese, about 0.05 to 0.25% zirconium, the balance substantially aluminum, incidental elements and impurities. The extrusion has a longitudinal yield strength of at least about 50 ksi and a longitudinal tensile ultimate strength of at least about 70 ksi. On a preferred basis, the extrusions of this invention include very low levels of both iron and silicon, typically on the order of less than 0.1 wt. % each, and more preferably about 0.05 wt. % or less iron and about 0.03 wt. % or less silicon.

Abstract: Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg?(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the three stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

Abstract: A system and method are disclosed for parallel compression and decompression of a bitstream. For compression, the bitstream is separated into a plurality of components, and the components are encoded using a compression algorithm. Packets are then constructed from the encoded components. At least one packet is associated with each encoded component and comprises header information and encoded data. The packets are combined into a packetized encoded bitstream. For decompression, the packets are separated from the packetized encoded bitstream using the header information. The packets are then decoded in parallel using a decompression algorithm to recover the encoded data. The plurality of components are reconstructed from the recovered encoded data and combined to-recover the bitstream.

Abstract: An alloy product having improved fatigue failure resistance, comprising about, by weight, 7.6 to about 8.4% zinc, about 2.0 to about 2.6% copper, about 1.8 to about 2.3% magnesium, about 0.088 to about 0.25% Zr, about 0.01 to about 0.09% Fe, and about 0.01 to about 0.06 w % Si the balance substantially aluminum and incidental elements and impurities The alloy product, suitable for aerospace applications, exhibits improved fatigue failure resistance than its 7055 counterpart of similar size, shape, thickness and temper.

Abstract: The present invention is directed to glassy matrix solid oral dosage forms useful for transmucosal oral administration of a nicotine active.

Abstract: The present invention is directed to highly controlled alloy composition relationship of a high purity Al—Mg—Cu alloy within the 2000 series aluminum alloys as defined by the Aluminum Association, wherein significant improvements are revealed in fracture toughness through plane strain, fracture toughness through plane stress, fatigue life, and fatigue crack growth resistance.

Abstract: A method embodiment of the invention tests revisions made to printer graphics interpreter software. A test suite of POSTSCRIPT, PCL, or other high-level printer language is input to a production version of a printer's internal interpreter software. A first bit-map is generated by the interpreter that is normally used to control each pixel in the printing of a page. The same test suite is fed to a work-in-progress revision of the printer's internal interpreter software. A second bit-map is generated. The first and second bit-maps are subtracted from one another. A difference bit-map is inspected. If only minor shifts of objects are noted, or if no differences at all are apparent, the work-in-progress revision is accepted as the new production standard. The second bit-map is used to replace the first. Otherwise, the work-in-progress revision of the printer's internal interpreter software is reworked to correct the printing interpretation errors it was making.

Abstract: This invention relates to a method for artificially aging 7000 Series A1 aerospace alloys to impart improved strength and/or corrosion resistance performance thereto. The method purposefully adds a second aging step or stage to a one-step tempering, or a third step/stage to a low-high, two-step aging operation. The added step/stage extends at about 225-275° F. for about 3-24 hours. More preferably, the added stage extends at about 250° F. for about 6 hours or more.

Abstract: A 7XXX series aluminum alloy having reduced quench sensitivity suitable for use in aerospace structural components, such as integral wing spars, ribs, extrusions and forgings comprises, in weight %: 6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, wherein Mg≦Cu+0.3, one or more of 0 to 0.4 Zr, up to 0.4 Sc, up to 0.2 Hf, up to 0.4 Cr, up to 1.0 Mn and the balance Al plus incidental additions including Si, Fe, Ti and the like plus impurities. By controlling the Mg content to 1.3 to 1.7 wt. %, limiting Mg≦Cu+0.3 and 6.5≦Zn≦8.5, the alloy provides significantly improved combined strength and fracture toughness in heavy gauges.

Abstract: Aluminum alloy products, such as plate, forgings and extrusions, suitable for use in making aerospace structural components like integral wing spars, ribs and webs, comprises about: 6 to 10 wt. % Zn; 1.2 to 1.9 wt. % Mg; 1.2 to 2.2 wt. % Cu, with Mg≦(Cu+0.3); and 0.05 to 0.4 wt. % Zr, the balance Al, incidental elements and impurities. Preferably, the alloy contains about 6.9 to 8.5 wt. % Zn; 1.2 to 1.7 wt. % Mg; 1.3 to 2 wt. % Cu. This alloy provides improved combinations of strength and fracture toughness in thick gauges. When artificially aged per the three stage method of preferred embodiments, this alloy also achieves superior SCC performance, including under seacoast conditions.

Abstract: The present invention is directed to highly controlled alloy composition relationship of a high purity Al—Mg—Cu alloy within the 2000 series aluminum alloys as defined by the Aluminum Association, wherein significant improvements are revealed in fracture toughness through plane strain, fracture toughness through plane stress, fatigue life, and fatigue crack growth resistance.

Abstract: The present invention is directed to highly controlled alloy composition relationship of a high purity Al—Mg—Cu alloy within the 2000 series aluminum alloys as defined by the Aluminum Association, wherein significant improvements are revealed in fracture toughness through plane strain, fracture toughness through plane stress, fatigue life, and fatigue crack growth resistance.

Abstract: A substantially unrecrystallized extrusion comprising about 3.6 to about 4.2 wt. % copper, about 1.0 to about 1.6 wt. % magnesium, about 0.3 to about 0.8 wt. % manganese, about 0.05 to about 0.25% zirconium, the balance substantially aluminum, incidental elements and impurities. The extrusion has a longitudinal yield strength of at least about 50 ksi and a longitudinal tensile ultimate strength of at least about 70 ksi. On a preferred basis, the extrusions of this invention include very low levels of both iron and silicon, typically on the order of less than 0.1 wt. % each, and more preferably about 0.05 wt. % or less iron and about 0.03 wt. % or less silicon.

Abstract: A method embodiment of the invention tests revisions made to printer graphics interpreter software. A test suite of POSTSCRIPT, PCL, or other high-level printer language is input to a production version of a printer's internal interpreter software. A first bit-map is generated by the interpreter that is normally used to control each pixel in the printing of a page. The same test suite is fed to a work-in-progress revision of the printer's internal interpreter software. A second bit-map is generated. The first and second bit-maps are subtracted from one another. A difference bit-map is inspected. If only minor shifts of objects are noted, or if no differences at all are apparent, the work-in-progress revision is accepted as the new production standard. The second bit-map is used to replace the first. Otherwise, the work-in-progress revision of the printer's internal interpreter software is reworked to correct the printing interpretation errors it was making.

Abstract: A method embodiment of the invention tests revisions made to printer graphics interpreter software. A test suite of POSTSCRIPT, PCL, or other high-level printer language is input to a production version of a printer's internal interpreter software. A first bit-map is generated by the interpreter that is normally used to control each pixel in the printing of a page. The same test suite is fed to a work-in-progress revision of the printer's internal interpreter software. A second bit-map is generated. The first and second bit-maps are subtracted from one another. A difference bit-map is inspected. If only minor shifts of objects are noted, or if no differences at all are apparent, the work-in-progress revision is accepted as the new production standard. The second bit-map is used to replace the first. Otherwise, the work-in-progress revision of the printers internal interpreter software is reworked to correct the printing interpretation errors it was making.

Abstract: A substantially unrecrystallized extrusion comprising about 3.6 to about 4.2 wt. % copper, about 1.0 to about 1.6 wt. % magnesium, about 0.3 to about 0.8 wt. % manganese, about 0.05 to about 0.25% zirconium, the balance substantially aluminum, incidental elements and impurities. The extrusion has a longitudinal yield strength of at least about 50 ksi and a longitudinal tensile ultimate strength of at least about 70 ksi. On a preferred basis, the extrusions of this invention include very low levels of both iron and silicon, typically on the order of less than 0.1 wt. % each, and more preferably about 0.05 wt. % or less iron and about 0.03 wt. % or less silicon.

Abstract: A tiltrotor aircraft includes a spanwise-flow redirector having a pair of flow-redirection panels respectively mounted on the aircraft's mid-fuselage area for rotation about a panel pivot axis between a stowed position and a deployed position. In the stowed position, each panel is substantially flush with an adjacent surface of the mid-fuselage area. In the deployed position, each panel is raised into the path of one of the inbound spanwise flows generated by the aircraft's rotors during hover operation, whereupon each panel redirects the respective one of the inbound spanwise flows either forward or aft of the other inbound spanwise flow. In this manner, the deployed panels prevent stagnation of the inbound spanwise flow atop the mid-fuselage area while further serving to minimize re-ingestion of merged spanwise flow into the rotors, resulting in decreased airframe download forces, increased rotor thrust, and reduced noise levels during hover operation.