Abstract: In order to simplify a system integration in a fuselage of an aircraft, the disclosure herein provides a production method for producing a load-bearing fuselage panel for a fuselage section of an aircraft fuselage in an area of an aircraft cabin, including manufacturing the fuselage panel to have a sandwich construction with an inner panel and an outer skin as shells and a filling panel embedded between the shells as a core, while configuring the outer skin as a part of a fuselage structure and the outer delimitation of the aircraft fuselage, configuring the inner panel for an interior space delimitation of the cabin, and integrating functional elements of the fuselage structure and the cabin and/or the aircraft into the filling panel. Preferably, the shells and the filling panel are connected to each other by a joining process while producing covalent bonds.

Abstract: This invention relates to the field of metallurgy, in particular to high strength weldable alloys with low density, of aluminium-copper-lithium system. These alloys can be used in air- and spacecraft engineering. The alloy comprises copper, lithium, zirconium, scandium, silicon, iron, beryllium, and at least one element from the group including magnesium, zinc, manganese, germanium, cerium, yttrium, titanium. A method for fabricating semiproducts is also provided.

Abstract: This invention relates to the field of metallurgy, in particular to high strength weldable alloys with low density, of aluminium-copper-lithium system. These alloys can be used in air- and spacecraft engineering. The alloy comprises copper, lithium, zirconium, scandium, silicon, iron, beryllium, and at least one element from the group including magnesium, zinc, manganese, germanium, cerium, yttrium, titanium. A method for fabricating semiproducts is also provided.

Abstract: This invention relates to the field of metallurgy, in particular to high strength weldable alloy with low density, of aluminium-copper-lithium system. Said invention can be used in air- and spacecraft engineering. The suggested alloy comprises copper, lithium, zirconium, scandium, silicon, iron, beryllium, and at least one element from the group including magnesium, zinc, manganese, germanium, cerium, yttrium, titanium. Also there is suggested the method for fabrication of semiproducts' which method comprising heating the as-cast billet prior to rolling, hot rolling, solid solution treatment and water quenching, stretching and three-stage artificial ageing.

Abstract: Weldable, high-magnesium-content aluminum-magnesium alloy consisting of at least 5-6% w/w magnesium (Mg), 0.05-0.15% w/w zirconium (Zr), 0.05-0.12% w/w manganese (Mn), 0.01-0.2% w/w titanium (Ti), 0.05-0.5% w/w of one or more elements from the scandium group and/or terbium (Tb), wherein at least scandium (Sc) is included, 0.1-0.2% w/w copper (Cu) and/or 0.1-0.4% w/w zinc (Zn), along with aluminum (Al), and unavoidable contamination does not exceed 0.1% w/w silicon (Si).

Abstract: A composite material includes a metallic second phase dispersed in a metallic matrix material. The metallic second phase has a grain structure that is at least partially martensitic. The second phase material is preferably an alloy of nickel and titanium, each present in the range from 48 to 52 atomic %, optionally in combination with further additives. The second phase particles can be present in the form of granular particles, wires, fibers, whiskers, or layers, making up 5 to 60 vol. % of the overall composite material. The matrix material is preferably an aluminum alloy. The composite material has a high damping capacity and a high tensile strength provided by the matrix, and a high damping capacity provided by the second phase. A method of making the composite material involves mixing a powdery matrix material and a powdery second phase material, and then heat and consolidating the mixture at a temperature of 400 to 700 ° C. and a pressure of 100 to 300 MPa.

Abstract: A weldable, high magnesium-content aluminum-magnesium alloy consisting essentially of at lest 5 to 6% by weight magnesium (Mg), 0.05 to 0.15% by weight zirconium (Zr), 0.7 to 1% by weight manganese (Mn), 0.01 to 0.2% by weight titanium (Ti), 0.005 to 0.5% by weight cerium (Ce), 0.05 to 0.5% by weight of one or more elements selected from the scandium group of the Periodic Table and/or terbium (Tb), wherein at least scandium (Sc) is included with or without terbium (Tb) and with or without 0.05 to 0.45% by weight of an element from the lanthanide series, the balance being aluminum (Al), and unavoidable contaminants not exceeding 0.2% by weight silicon (Si).

Abstract: A weldable, corrosion resistant aluminum-magnesium alloy consisting essentially of 3 to 5% by weight magnesium (Mg), 0.05 to 0.15% by weight zirconium (Zr), 0.05 to 0.12% by weight manganese (Mn), 0.01 to 0.2% by weight titanium (Ti), 0.05 to 0.5% by weight of one or more elements selected from the scandium group of the Periodic Table and/or terbium (Tb), wherein at least 0.15% by weight scandium (Sc) is included with or without terbium (Tb) and with or without 0.05 to 0.35% by weight of one or more elements from the lanthanide series, the balance being aluminum (Al), and unavoidable contaminants not exceeding 0.2% by weight silicon (Si).