Abstract: Extrados structural element made from an aluminum, copper and lithium alloy and method for manufacturing same. An alloy with composition (in wt %) 4.2-5.2 Cu, 0.9-1.2 Li, 0.1-0.3 Ag, 0.1-0.25 Mg, 0.08-0.18 Zr, 0.01-0.15 Ti, an Fe and Si content level less than or equal to 0.1% each, and other element with content level less than or equal to 0.05% each and 0.15% in total, is poured, homogenized, deformed hot, placed in a solution at a temperature of at least 515° C., pulled from 0.5 to 5% and annealed. The combination of magnesium, copper and manganese content with the temperature in solution can reach an advantageous elasticity under compression limit. Products having a thickness of at least 12 mm have, in the longitudinal direction, an elasticity under compression limit of at least 645 MPa and an elongation of at least 7%.

Abstract: The invention relates to a product based on an aluminium alloy comprising, as percentages by weight, 4.0 to 4.6% by weight of Cu, 0.7 to 1.2% by weight of Li, 0.5 to 0.65% by weight of Mg, 0.10 to 0.20% by weight of Zr, 0.15 to 0.30% by weight of Ag, 0.25 to 0.45% by weight of Zn, 0.05 to 0.35% by weight of Mn, at most 0.20% by weight of Fe+Si, at least one element selected from Cr, Sc, Hf, V and Ti, the amount of said element, if selected, being from 0.05 to 0.3% by weight for Cr and for Sc, 0.05 to 0.5% by weight for Hf and for V and 0.01 to 0.15% by weight for Ti, the other elements being at most 0.05% by weight each and 0.15% by weight in total, the remainder being aluminium. The invention also relates to a method for obtaining such a product and to the use thereof as an aircraft structural element.

Abstract: The disclosure provides for plate having a thickness of at least 80 mm comprising aluminium alloy as a percentage by weight %: Cu: 2.0-6.0; Li: 0.5-2.0; Mg: 0-1.0; Ag: 0-0.7; Zn 0-1.0; and at least one element selected from Zr, Mn, Cr, Sc, Hf and Ti, the amount of said element, if selected, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8% wt % t for Mn, 0.05 to 0.3 wt % for Cr and for Sc, 0.05 to 0.5 wt % Hf and 0.01 to 0.15% wt % for Ti, Si?0.1; Fe?0.1; others ?0.05 each and ?0.15 in total, wherein the aged state logarithmic fatigue mean measured at mid-thickness in the LT direction on smooth specimens with a maximum stress amplitude of 242 MPa, a frequency of 50 Hz, a stress ratio of R=0.1 of at least 250,000 cycles.

Abstract: The invention concerns a method for forming by welding along a flat surface an article. The method according to the invention is particularly useful to improve strength and elongation of welded joints obtained by linear friction welding. Structural articles of aircrafts obtained with the method of the invention are advantageous, in particular aircraft structural members.

Abstract: The invention concerns a method for forming by welding along a flat surface an article. The method according to the invention is particularly useful to improve strength and elongation of welded joints obtained by linear friction welding. Structural articles of aircrafts obtained with the method of the invention are advantageous, in particular aircraft structural members.

Abstract: The invention relates to an extrados structural element made from an aluminum, copper and lithium alloy and a method for manufacturing same. In the method according to the invention, an alloy with composition (in wt %) 4.2 to 5.2 Cu, 0.9 to 1.2 Li, 0.1 to 0.3 Ag, 0.1 to 0.25 Mg, 0.08 to 0.18 Zr, 0.01 to 0.15 Ti, optionally up to 0.2 Zn, optionally up to 0.6 Mn, an Fe and Si content level less than or equal to 0.1% each, and other element with a content level less than or equal to 0.05% each and 0.15% in total, the aluminum is poured, homogenized, deformed hot and optionally cold, placed in a solution at a temperature of at least 515° C., pulled from 0.5 to 5% and annealed. The combination in particular of the magnesium, copper and manganese content with the temperature in solution can reach a very advantageous elasticity under compression limit.

Abstract: The invention relates to a method for manufacturing a thin sheet having a thickness of 0.5 to 3.3 mm and an essentially non-recrystallized structure made of aluminum-based alloy.