Abstract: A pressure bulkhead (1) for an aircraft fuselage (3) having a sandwich structure (5) which defines a central axis (9) and which extends between a circumferential edge area (7), wherein the sandwich structure (5) includes an inner cover layer (13), an outer cover layer (17), and a core layer (19), which extends between the inner and outer cover layers (13, 17) and connects them.

Abstract: Described and illustrated is a pressure bulkhead for an aircraft fuselage, comprising a sandwich structure defining a central axis and extending between a circumferential border area which is configured for being mounted to a fuselage shell, wherein the sandwich structure comprises an inner face sheet extending perpendicularly with respect to the central axis, an outer face sheet opposite the inner face sheet, extending perpendicularly with respect to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet, wherein the inner face sheet, when viewed in a radial cross section along the central axis, has an even shape.

Abstract: A pressure bulkhead for an aircraft fuselage including a sandwich structure defining a central axis and extending between a circumferential border area, the sandwich structure including an inner face sheet and an outer face sheet extending transverse to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet. The pressure bulkhead can receive pressure loads and can be used as a structural bearing element for receiving loads introduced by other structural parts. The inner face sheet and/or the outer face sheet has a corrugated shape. The distance between the outer face sheet and the inner face sheet increases and subsequently decreases from the border area to a central area about the central axis, forming a thickened area where the distance between the outer face sheet and the inner face sheet has a peak.

Abstract: An aircraft structural component having a skin element, including an inner surface, a multitude of transverse stiffening elements, which lie against the inner surface of the skin element, and a multitude of longitudinal stiffening elements, perpendicular to the transverse stiffening elements against the inner surface of the skin element, wherein between a first and a second transverse stiffening element and also between a first and a second longitudinal stiffening element, a first skin section is defined. An aircraft structural component is provided with the quantity of the longitudinal stiffening elements reduced. A first applied reinforcement includes a core layer having a contour line running along the circumference of the skin element, the first applied reinforcement including a face sheet surrounding the core layer on the side thereof which faces away from the skin element, which face sheet is connected to the skin element along the core layer contour line.

Abstract: The invention relates to a method for tolerance compensation between two fiber composite component parts (1, 3) for aircraft. In order to compensate in simplified fashion tolerances between two fiber composite component parts being joined, the method according to the invention has the steps: a) manufacturing the first fiber composite component part (1) wherein an assembly surface (2) can have tolerance deviations, b) manufacturing a tooling insert (7) from a surface geometry of the assembly surface (2) c) manufacturing the second fiber composite component part (3) by means of the tooling insert (7) wherein a surface geometry of a contact surface (9) of the second fiber composite component part (3) corresponds substantially with the surface geometry of the assembly surface (2), and d) joining the first fiber composite component part (1) to the second fiber composite component part (3) in the area of the assembly surface (2) and contact surface (9).

Abstract: A device for improving the breathing air quality for the crew and/or the passengers in an aircraft cabin includes an oxygen source, a water source and a feed line, wherein the feed line is connectable to the oxygen source and the water source in order to oxygenate and/or humidify air that is introduced into the feed line. The feed line is further connected to an inlet port of a locally delimited area of the aircraft cabin and adapted so as to feed oxygenated and/or humidified air to the locally delimited area of the aircraft cabin.

Abstract: The present invention relates to an apparatus and a method to activate a binder on a semi-finished fiber material containing carbon fibers or on a preform. The binder is applied to the semi-finished fiber material or the fiber preform and subsequently activated through increasing the temperature by conducting an electrical current through the carbon fibers of the preform.

Abstract: The invention relates to a method for tolerance compensation between two fibre composite component parts (1, 3) for aircraft. In order to compensate in simplified fashion tolerances between two fibre composite component parts being joined, the method according to the invention has the steps: a) manufacturing the first fibre composite component part (1) wherein an assembly surface (2) can have tolerance deviations, b) manufacturing a tooling insert (7) from a surface geometry of the assembly surface (2) c) manufacturing the second fibre composite component part (3) by means of the tooling insert (7) wherein a surface geometry of a contact surface (9) of the second fibre composite component part (3) corresponds substantially with the surface geometry of the assembly surface (2), and d) joining the first fibre composite component part (1) to the second fibre composite component part (3) in the area of the assembly surface (2) and contact surface (9).

Abstract: A device (10) for improving the breathing air quality for the crew and/or the passengers in an aircraft cabin (12) comprises an oxygen source (16), a water source (18) and a feed line (14), wherein the feed line (14) is connectable to the oxygen source (16) and the water source (18) in order to oxygenate and/or humidify air that is introduced into the feed line (14). The feed line (14) is further connected to an inlet port (24) of a locally delimited area (26) of the aircraft cabin (12) and adapted so as to feed oxygenated and/or humidified air to the locally delimited area (26) of the aircraft cabin (12).

Abstract: A system comprises an H2/O2 steam generator (2) for generating superheated steam which is either fed directly to a gas turbine (8) to bring it to a rotary speed that is sufficient to result in a compressed-air ratio in the gas turbine that allows operation of the gas turbine with a fuel, or which superheated steam is fed to a compressed-air generator (4) for generating compressed-air, wherein the generated compressed-air is fed to a compressed-air system (7), for example of an aircraft, or is used for starting a gas turbine or for other compressed-air systems.

Abstract: The present invention relates to an apparatus and a method to activate a binder on a semi-finished fiber material containing carbon fibers or on a preform. The binder is applied to the semi-finished fiber material or the fiber preform and subsequently activated through increasing the temperature by conducting an electrical current through the carbon fibers of the preform.