Abstract: In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length.

Abstract: The present invention is directed to a substantially unrecrystallized rolled aluminum alloy product, obtained from a plate with a thickness of at least 30 mm, comprising 2.2 to 3.9 wt. % Cu, 0.7 to 2.1 wt. % Li, 0.2 to 0.8 wt. % Mg, 0.2 to 0.5 wt. % Mn, 0.04 to 0.18 wt. % Zr, less than 0.05 wt. % Zn, and optionally 0.1 to 0.5 wt. % Ag, remainder aluminum and unavoidable impurities having a low propensity to crack branching during L-S a fatigue test. A product of the invention has a crack deviation angle ? of at least 20° under a maximum equivalent stress intensity factor Keff max of 10 MPa ?m for a S-L cracked test sample under a mixed mode I and mode II loading wherein the angle ? between a plane perpendicular to the initial crack direction and the load direction is 75°.

Abstract: A process for making Al—Zn—Mg alloy products, and products formed according to such processes are disclosed. The present invention provides a product having an improved compromise between mechanical characteristics and corrosion strength.

Abstract: Provided herein is a method for manufacturing a worked product comprising a fiber sensor therein. Also provided is a wrought product comprising a fiber sensor as well as structural elements and other products including fuselage skin and a wing panel.

Abstract: The present invention is directed to a substantially unrecrystallized rolled aluminum alloy product, obtained from a plate with a thickness of at least 30 mm, comprising 2.2 to 3.9 wt. % Cu, 0.7 to 2.1 wt. % Li, 0.2 to 0.8 wt. % Mg, 0.2 to 0.5 wt. % Mn, 0.04 to 0.18 wt. % Zr, less than 0.05 wt. % Zn, and optionally 0.1 to 0.5 wt. % Ag, remainder aluminum and unavoidable impurities having a low propensity to crack branching during L-S a fatigue test.

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.

Abstract: In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length.

Abstract: A Glare type composite laminated sandwich panel comprising (i) aluminum (ii) glass fibre with adhesive (iii) aluminum is disclosed. According to the present invention, at least one of the aluminum sheets is preferably made of an aluminum non-heat treatable alloy type Al—Mg with a magnesium content of between 4 and 6%. These sandwich panels have mechanical characteristics similar to sandwich panels comprising sheets with a heat treatable alloy. Panels of the present invention further generally have better corrosion resistance and are less expensive than those made with heat treatable alloys such as 2xxx and 7xxx type alloys.

Abstract: A structural member comprising at least two aluminum alloy parts displaying different property balances, said at least two parts being welded and wherein one of said parts either is (i) selected from an aluminum alloy different from the other of said at least two parts and/or (ii) is selected from an initial temper different from the other of said at least two parts, and wherein at least one of said at least two parts has been pre-aged prior to being welded, and, wherein said structural member has undergone a post-welding thermal treatment conferring a final temper to each of said at least two parts. The parts are advantageously welded by friction stir welding. Another subject of the invention is a method for manufacturing a structural member.

Abstract: A process for making Al—Zn—Mg alloy products, and products formed according to such processes are disclosed. The present invention provides a product having an improved compromise between mechanical characteristics and corrosion strength.

Abstract: The present invention relates to a work-hardened product, and particularly a rolled, extruded and/or forged product made of an alloy with composition (% by weight): Zn 6.7-7.3% Cu 1.9-2.5% Mg 1.0-2.0% Zr 0.04-0.15% Fe ?0.15 Si ?0.15 other elements ?0.05 each and ?0.15 total, remainder aluminium and wherein Mg/Cu<1. The product is preferable treated by solution heat treatment, quenching, cold working and artificial aging. Cold working may be achieved by controlled tension and/or cold transformation, for example rolling or drawing. The product may be used, for example, as an aircraft structural member.

Abstract: A Glare type composite laminated sandwich panel comprising (i) aluminum (ii) glass fibre with adhesive (iii) aluminum is disclosed. According to the present invention, at least one of the aluminum sheets is preferably made of an aluminum non-heat treatable alloy type Al—Mg with a magnesium content of between 4 and 6%. These sandwich panels have mechanical characteristics similar to sandwich panels comprising sheets with a heat treatable alloy. Panels of the present invention further generally have better corrosion resistance and are less expensive than those made with heat treatable alloys such as 2xxx and 7xxx type alloys.

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.