Airbus Deutschland Gmbh

Eurocopter Deutschland Gmbh

Johnson Controls Components Gmbh & Co Kg

Airbus Operations Gmbh

Deutsches Zentrum Fur Luft-und Raumfahrt E.v.

Adient Luxembourg Holding S.a.r.l.

Jens Bold

Axel Fink

Lars Kramm

Harald Wolsiefer

Ulrich Riedel

Willem Jan Ter Steeg

Guenther Klockow

Klaus Edelmann

Vernon Holmes

Markus Kleineberg

Alexander Engleder

Christian Hühne

Georg-Ludwig Fischer

Matthias Grote

Olaf Steffen

Christian Ückert

Ivonne Bartsch

Lothar Pollithy

Werner Bluem

Thomas Wurl

A composite component () for a vehicle seat (), in particular a motor vehicle seat, having a plurality of fabric layers () of a fiber material and a matrix material () fixing the fabric layers (). The outer component contour of the composite component () is at least in some sections formed by a fabric strand () embedded into the matrix material (). A vehicle seat (), in particular a motor vehicle seat, includes a composite component, in particular with a backrest structure () designed as the composite component.

Composite component for a vehicle seat, and vehicle seat

A composite component () for a vehicle seat (), in particular for a motor vehicle seat, includes a plurality of fabric layers () of a fibrous material, a matrix material () securing the fabric layers (), and an insert part (), disposed between at least two of the fabric layers (), for locally reinforcing the composite component. An insert strand () is disposed at least in sections along an edge or an edge surface () of the insert part (). A vehicle seat () includes the composite component, in particular with a back structure () designed as a composite component.

Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

Reinforcement beam as well as method and fiber laminate for manufacturing the reinforcement beam

A method for making a window frame for installation in the exterior shell of an aircraft, which comprises at least one outer flange, an inner flange, and a vertical flange arranged perpendicular to and between these two flanges, contemplates that first a semifinished part comprising multiple, individual substructures is made, which next is inserted into a molding tool, into which, under pressure and temperature, resin is injected, and that the component made in this manner subsequently is hardened in the molding tool. The semifinished part has a layer structure, which comprises a web material, fiber bundles, or a combination of fiber bundles and web material.

Method for making window frame

A window frame () for installation in the exterior () of an aircraft, which comprises in each case at least one outer flange (), one inner flange, and one vertical flange () arranged perpendicular between these flanges, is manufactured from a fiber-reinforced synthetic resin, in which, first, a semifinished part comprising fiber material is inserted into a molding tool, in which, under pressure and temperature, resin is injected, and subsequently, the component made in this manner is hardened in the molding tool. The semifinished part can have a layer structure either made from a webbing material, from fiber bundles, or from a combination of fiber bundles and a webbing material.

Window frame for aircraft

A window frame for installation in the exterior shell of an aircraft, which comprises one outer flange, an inner flange, and a vertical flange extending between flanges. A window frame is fixed in its position via a plurality of holder elements being arranged substantially equidistance from each other over the periphery of the window frame, being distributed on the outer flange of the window frame. Each of the holder elements comprises a base plate having a face, a pin, a pin extending outwardly from the face of the base plate and a pin to, a downholder clip. The clip may be adapted for a press fit engagement with the pin. The outer surfaces of the pin include a sawtooth-like structure, which engages with hook-shaped clamping elements flexibly formed on the downholder clip and over which an annular locking element is displaced. The holder elements may include a thermoplastic material, which may be provided with reinforcement fibers and may be die cast. Before installation of the window frame in the aircraft, the base plates of the holder elements are adhered to the outer flange of the window frame, and upon mounting of the window frame to an aircraft structure, the outer flange is riveted to an exterior shell of the aircraft.

A window frame () for installation in the exterior shell of an aircraft comprises in each case at least one outer flange (), one inner flange (), and one vertical flange () arranged perpendicular to and between these flanges (), wherein the connection with the aircraft structure () is realized via the outer flange () and wherein on the inner flange (), a window element () to be held is attached, which is held via the vertical flange (). The window frame () comprises resin reinforced with unidirectionally arranged fiber bundles (), wherein the progression of the fiber bundles in the three regions of the outer flange (), inner flange (), and vertical flange (), respectively, follow the mechanical load direction. For manufacturing, a semifinished part made from unidirectionally arranged fiber bundles is inserted into a molding tool (), in which, under pressure and temperature, resin is injected, and the component made in this manner is hardened subsequently in the molding tool().

An aircraft door has an inner framework integrally connected to an outer skin by simultaneously casting the framework and the skin in a mold that holds a single core for each frame element in the form of a rib in a freight door or a beam in a passenger door. The ribs extend circumferentially relative to a longitudinal central axis of the aircraft. The beams extend in parallel to the central aircraft axis. The single core is selected from at least one core type and four core types at the most. The frame elements in the form of ribs or beams have open arches for a considerable weight reduction.

Aircraft door and mold for casting the door

An aircraft door has a trough substantially closed by an outer planking ( ) except for a vent that vents the space enclosed by the trough and the planking to the atmosphere outside of the aircraft. The door also includes a door stiffening door framing that is preferably but not necessarily mounted inside the trough or between a radially inner wall of the trough and an inner door cladding or covering. The trough is formed by a radially inwardly recessed portion of the outer door skin.

Aircraft door

The skin of an airplane door conforms in use to a surrounding surface contour of an airplane fuselage. The skin is connected with a door frame which has supports arranged in a longitudinal direction of the fuselage and spaced with respect to one another in a circumferential direction. During flight the skin and door frame are exposed to a pressure load direction. To provide the skin of an airplane door with a clearly smaller dimension for the purpose of a light construction thereby avoid displacements on the skin, the skin and door frame are preformed against an in use pressure load direction. During the flight at cruising altitude, the door has essentially no displacements with respect to the surrounding surface contour of the fuselage, and thus essentially no displacements occur which could increase the flow resistance of the skin. Relative to a material, it is possible to thus construct the skin in a smaller thickness than in the case of known doors, but disturbing displacements on the skin are nevertheless essentially avoided while permitting a weight reduction of the door.

Growing community of inventors

Hamburg, Germany

Jens Bold