Airbus Operations Gmbh

Airbus Deutschland Gmbh

Csir

Airbus (sas)

Berend Schoke

Heinz-Peter Busch

Michael Doecker

Peter Turanski

Stephen Anthony Chapple

Wilfried Michaelis

Hans-Jürgen Schelling

Jürgen Langediers

Michael Döcker

Jens Kluesener

Rajesh Anandjiwala

Werner Buck

Wilko Östereich

Maya Jacob John

Falk Brinkmann

Thomas Engel

Marcel Meyer

Jens KLÜSENER

A method for producing a composite component including a bottom layer, cover layer and honeycomb structure, including applying the honeycomb structure to the bottom layer wherein honeycomb chambers are formed. Honeycomb chambers are filled in a reinforcement region with a granular material and granular material is removed from other honeycomb chambers wherein each honeycomb chamber is filled up to a granular-material filling height and honeycomb chambers outside the reinforcement region are free of granular material. The cover layer is applied to the honeycomb structure wherein the honeycomb chambers are closed. The composite component is heated so the granular material in the honeycomb chambers expands to fill it with granular material and the cover layer, the bottom layer, the honeycomb structure and the expanded granular material harden, the density of the expanded granular material in the honeycomb chambers filled with granular material being dependent on the granular-material filling height.

Method for producing a composite component

A plastics material component for an aircraft includes (i) a substrate, which comprises one or more thermosetting plastics materials, and (ii) one or more layers which are applied to the substrate, at least one layer S1 comprising mica. A method for producing the plastics material component includes providing a substrate including at least one thermosetting plastics material or one polymer which is crosslinked to form a thermosetting plastics material, and applying one or more layers to the substrate, wherein at least one layer includes mica. The mica-containing layer is applied directly to the substrate and the application is carried out before and/or during the curing of the thermosetting plastics material.

Use of inorganic particles to produce a barrier layer on aircraft components

A method of fabricating an artifact () includes treating natural fibers () with a non-halogenated flame retardant agent (), the fibers () also being treated with a smoke suppressant (). At least one pre-preg is formed () from the treated natural fibers and from a resin composition () including a smoke suppressant () admixed therein (). An uncured artifact is formed from a core or substrate () and the pre-preg, which provides a skin, and is cured (). A non-fibrous silicate fire resistant material () is introduced by: (i) admixing the fire resistant material with the resin composition, and/or (ii) applying the fire resistant material to an outer surface of the pre-preg or an outer surface of the skin of the uncured artifact, and/or (iii) applying the fire resistant material to an outer surface of the skin of the cured artifact. The invention extends to a flame-proofed artifact ().

Flame-proofed artefact and a method of manufacture thereof

A sandwich panel with at least one insert for forming a local reinforcement, which insert is smaller than a distance between the cover layers of the sandwich panel. A difference between the distance between the cover layers and a length of an extension of the insert including a previously viscous expansion compound with adhesive properties, which expansion compound has solidified during the pressing of the sandwich panel, is compensated for. A sandwich panel with at least one previously elastic insert whose original extension as a result of deformation during pressing of the sandwich panel is reduced. A method for producing such sandwich panels.

Sandwich panels and method for producing sandwich panels

A facing arrangement for a hold of an aircraft or spacecraft. The facing arrangement comprises a first and a second panel which form a gap between them; a first mounting part which is to be attached to a primary structure of the hold and which has at least one locking arrangement, and a second mounting part which has at least one counter locking arrangement. The locking arrangement and/or the counter locking arrangement passing, at least in portions, through the gap between the first and the second panel. The locking arrangement and the counter locking arrangement being locked together in order to connect the first mounting part to the second mounting part for holding the first and second panels between the first mounting part and the second mounting part.

Facing arrangement and aircraft or spacecraft

The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.

Fireproof bulkhead of a highly porous structure with intumescent coating and method for its production

A method for the repair of a sandwich plate having a core structure, a top surface layer and a bottom surface layer and a plurality of honeycomb-shaped cells includes providing at least one penetrating drill hole in at least one of the top surface layer and the bottom surface layer above one of the plurality of honeycomb-shaped cells in a damaged region of the sandwich plate, injecting a stabilising material into the honeycomb-shaped cell, and filling the damaged region with a filler material.

Method and a spraying device for the repair of a sandwich plate

A fire protection device for an aircraft or spacecraft is disclosed. The fire protection device can include a fireproof bulkhead and an adjusting device, the fireproof bulkhead can be adjusted from a ventilating position I into a screening position II. This may prevent a stream of smoke and heat from penetrating into the cabin when there is a fire underneath the fuselage.

Fire protection device for an aircraft or spacecraft

A fire-retarding cable conduit for electrical lines in regions potentially exposed to fire in aircraft, has a tubular base body including an interior space for accommodating the electrical lines and may include a sheath. The base body comprise a plastic foam material, which in the event of a fire is intumescent the intumescent foam may form a material that is substantially free of plastic when exposed to fire. A continuous longitudinal slit may be provided for inserting the electrical lines into the tubular base body and may use a form that protects the lines during exposure to fire.

Growing community of inventors

Twistringen, Germany

Berend Schoke