Abstract: A fabric cutting system and/or method can include a mandrel having a body and first and second legs, a centered chuck, and an offset chuck, each chuck configured to receive either one of the legs or body to rotatingly support the mandrel between the chucks. When one of the legs is inserted into the centered chuck and the mandrel body is inserted into the offset chuck, the mandrel can be rotated and the fabric mounted on the mandrel can be cut about the leg at a location beyond the end of the other leg. One of the legs can include a leg extension removable from a leg base that when removed allows the other leg to be cut beyond the end of the leg base. The fabric can be cut with a cutting laser, which may be a multi-axis laser, and/or have low power.

Abstract: The present invention relates to a method and an apparatus for data migration of a first file system in a data storage system comprising a plurality of client computers 100, a first file system managing unit 310 for managing the first file system and being connected to the plurality of client computers 100, and a second file system managing unit 410 for managing a second file system and being connected to the first file system managing unit 310, the second file system comprising a plurality of data files and the first file system comprising a plurality of external link objects, each external link object of the first file system being associated with a respective data file of the second file system for enabling client access to the respective data file of the second file system.

Abstract: The present invention relates to a method and an apparatus for providing a virtualized file system enabling indirect access to a second file system in a data storage system comprising a plurality of client computers 100 and a second file system managing unit 410 for managing the second file system and enabling client access to the second file system, the method comprising interconnecting a first file system managing unit 310 between the plurality of client computers 100 and the second file system managing unit 410, creating a first directory /root in a first file system managed by the first file system managing unit 310, associating a first directory /root of the second file system with the first directory /root of the first file system, enabling on-demand virtualization of the second file system by the first file system managing unit 310 based on client requests received from the client computers 100 at the first file system managing unit 310 and based on the association between the first directory of the fi

Abstract: An aluminum alloy comprising 2.1 to 2.8 wt. % Cu, 1.1 to 1.7 wt. % Li, 0.1 to 0.8 wt. % Ag, 0.2 to 0.6 wt. % Mg, 0.2 to 0.6 wt. % Mn, a content of Fe and Si less or equal to 0.1 wt. % each, and a content of unavoidable impurities less than or equal to 0.05 wt. % each and 0.15 wt. % total, and the alloy being substantially zirconium free.

Abstract: A fabric cutting system and/or method can include a mandrel having a body and first and second legs, a chuck, the chuck configured to receive either one of the legs or body to rotatingly support the mandrel. The mandrel can be rotated and the fabric mounted on the mandrel can be cut about the leg at a location beyond the end of the other leg. One of the legs can include a leg extension removable from a leg base that when removed allows the other leg to be cut beyond the end of the leg base. The fabric can be cut with a cutting laser, which may be a multi-axis laser, and/or have low power.

Abstract: An aluminum alloy comprising 2.1 to 2.8 wt. % Cu, 1.1 to 1.7 wt. % Li, 0.1 to 0.8 wt. % Ag, 0.2 to 0.6 wt. % Mg, 0.2 to 0.6 wt. % Mn, a content of Fe and Si less or equal to 0.1 wt. % each, and a content of unavoidable impurities less than or equal to 0.05 wt. % each and 0.15 wt. % total, and the alloy being substantially zirconium free.

Abstract: A fabric cutting system and/or method can include a mandrel having a body and first and second legs, a centered chuck, and an offset chuck, each chuck configured to receive either one of the legs or body to rotatingly support the mandrel between the chucks. When one of the legs is inserted into the centered chuck and the mandrel body is inserted into the offset chuck, the mandrel can be rotated and the fabric mounted on the mandrel can be cut about the leg at a location beyond the end of the other leg. One of the legs can include a leg extension removable from a leg base that when removed allows the other leg to be cut beyond the end of the leg base. The fabric can be cut with a cutting laser, which may be a multi-axis laser, and/or have low power.

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: A fabric cutting system and/or method can include a mandrel having a body and first and second legs, a centered chuck, and an offset chuck, each chuck configured to receive either one of the legs or body to rotatingly support the mandrel between the chucks. When one of the legs is inserted into the centered chuck and the mandrel body is inserted into the offset chuck, the mandrel can be rotated and the fabric mounted on the mandrel can be cut about the leg at a location beyond the end of the other leg. One of the legs can include a leg extension removable from a leg base that when removed allows the other leg to be cut beyond the end of the leg base. The fabric can be cut with a cutting laser, which may be a multi-axis laser, and/or have low power.

Abstract: A rolled or forged Al—Zn—Cu—Mg aluminum-based alloy wrought product having a thickness from 2 to 10 inches. The product has been treated by solution heat-treatment, quenching and aging, and the product comprises (in weight-%): Zn 6.2-7.2, Mg 1.5-2.4, Cu 1.7-2.1. Fe 0-0.13, Si 0-0.10, Ti 0-0.06, Zr 0.06-0.13, Cr 0-0.04, Mn 0-0.04, Mn 0-0.04, impurities and other incidental elements ?0.05 each. Alloys per se and aircraft and aerospace uses, as well as methods of making products are also disclosed.

Abstract: The invention relates to a manufacturing process for flat-rolled products made of an alloy containing aluminum, including the steps of production, casting, homogenization, rolling at temperature greater than 400° C., solution heat treating, quenching, stretching between 2 and 3.5% and aging. The invention also relates to flat-rolled products obtained by this process, which offer a favorable compromise of properties between mechanical resistance under compression and stretching and fracture toughness. The products according to the invention are useful in particular for the manufacture of upper wing skins.

Abstract: The invention relates to a wrought product such as an extruded, rolled and/or forged aluminum alloy-based product comprising, in weight %: Cu: 3.0-3.9; Li: 0.8-1.3; Mg; 0.6-1.0; Zr: 0.05-0.18; Ag: 0.0-0.05; Mn: 0.0-0.5; Fe+Si?0.20; Zn?0.15; at least one element from among: Ti: 0.01-0.15; Sc: 0.05-0.3; Cr: 0.05-0.3; Hf: 0.05-0.5; other elements ?0.05 each and ?0.15 total, remainders aluminum. The invention also relates to the process for producing said product. The products according to the invention are particularly useful in the production of thick aluminum products intended for producing structural elements in the aeronautical industry.

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 invention relates to a wrought product such as an extruded, rolled and/or forged aluminum alloy-based product, comprising, in weight %: Cu: 3.0-3.9; Li: 0.8-1.3; Mg: 0.6-1.0; Zr: 0.05-0.18; Ag: 0.0-0.5; Mn: 0.0-0.5; Fe+Si?0.20; Zn?0.15; at least one element from among: Ti: 0.01-0.15; Sc: 0.05-0.3; Cr: 0.05-0.3; Hf: 0.05-0.5; other elements ?0.05 each and ?0.15 total, remainder aluminum. The invention also relates to the process for producing said product. The products according to the invention are particularly useful in the production of thick aluminum products intended for producing structural elements in the aeronautical industry.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenisation, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

Abstract: The present invention includes a process for manufacturing metal sheets or plates and a machined metal part as well as machined products, structural components and their uses in various applications. Manufacture of a metal sheet or plate by a process of the present invention comprises casting of a rolling ingot, optionally followed by homogenization, one or more hot or cold rolling operations, optionally separated by one or more re-heating operations, to obtain a sheet, or plate and optionally one or more sheet or plate cutting or finishing operations. The sheet is pre-machined on one or both sides so as to obtain a pre-machined stock, and subjected to solution heat treatment, quenching treatment, and optionally, one or more of the following steps: controlled stretching, aging treatment, and/or cutting.

Abstract: A low density aluminum based alloy useful in aircraft structure for fuselage sheet or light-gauge plate applications which has high strength, high fracture toughness and high corrosion resistance, comprising 2.7 to 3.4 weight percent Cu, 0.8 to 1.4 weight percent Li, 0.1 to 0.8 weight percent Ag, 0.2 to 0.6 weight percent Mg and a grain refiner such as Zr, Mn, Cr, Sc, Hf, Ti or a combination thereof, the amount of which being 0.05 to 0.13 wt. % for Zr, 0.1 to 0.8 wt. % for Mn, 0.05 to 0.3 wt. % for Cr and Sc, 0.05 to 0.5 wt. % for Hf and 0.05 to 0.15 wt. % for Ti. The amount of Cu and Li preferably corresponds to the formula Cu(wt. %)+5/3 Li(wt. %)<5.2.

Abstract: An aluminum alloy having improved strength and ductility, comprising: Cu 3.5-5.8 wt. %, Mg 0.2-1.5 wt. % Mn 0.2-0.5 wt. % Ag 0.2-0.8 wt. % Ti 0.02-0.12 wt. % and optionally one or more selected from the group consisting of Cr 0.1-0.8 wt. %, Hf 0.1-1.0 wt. %, Sc 0.03-0.6 wt. %, and V 0.05-0.15 wt. %, balance aluminum and incidental elements and impurities, and wherein the alloy is substantially zirconium-free.

Abstract: The invention relates to alloys and associated products which are laminated, extruded or forged in Al—Zn—Mg—Cu alloy. Alloys of the invention generally comprise (in mass percentage): a) Zn 8.3-14.0=Cu 0.3-4.0=Mg 0.5-4.5 Zr 0.03-0.15 Fe+Si<0.25 b) at least one element selected from the group consisting of Sc, Hf, La, Ti, Ce, Nd, Eu, Gd, Tb, Dy, Ho, Er, Y and Yb, the content of each elements; if included, being between 0.02 and 0.7%, and c) the aluminum remainder and inevitable impurities, and wherein Mg/Cu<2.4 and (7.7?0.4 Zn)>(Cu+Mg)>(6.4?0.4 Zn). Products of the present invention are useful as structural elements (for example wing unit caisson, wing unit extrados) in aeronautical construction.

Abstract: A method for manufacturing aluminium alloy parts with precipitation hardening including friction stir welding of at least two elements made from the same alloy or different alloys, solution heat treatment, and quenching of welded parts, in which the elements are subjected to heat treatment before welding at temperature T for at least 2t1, t1 being defined as the minimum treatment duration at temperature T leading to a specific melting peak energy defined by AED equal to less than 1 J/g. A method according to the invention substantially avoids an increase in the grain size following solution heat treatment after welding. The invention further relates to novel aluminum materials as well as uses therefor.