Airbus Operations Gmbh

Airbus Deutschland Gmbh

Martin Staub

Markus Schumacher

Andreas Heidtmann

Thorsten Otto

Juergen Filsinger

Andreas Gessler

Jana Witt

Tim Leeraar

Klaus Von Varendorff

Arne Mashoff

A cabin monument for an aircraft includes a floor panel, which forms a base surface of the cabin monument, and a surrounding sidewall which defines an interior space of the cabin monument. The surrounding sidewall is assembled from a first wall part and a second wall part which is coupled to this. Provision is made on at least one of the wall parts for a fixing section which is overlapped by the floor panel. Also described is an aircraft which features such a cabin monument.

Cabin monument for an aircraft

A cabin monument for an aircraft. The cabin monument has a framework with a base frame and a frame structure connected to the base frame, and side walls fastened to the frame structure. By fastening the side walls to the structural struts of the frame structure, a mechanical load acting on the cabin monument is distributed between the framework and the side walls.

The invention relates to a method for producing a composite component reinforced by stiffening elements. Composite component is produced by the inside gluing of a monolithic component to a multiplicity of stiffening elements by means of an adhesive suitable for this particular application. Stiffening elements are formed with a fiber reinforced, amorphous thermoplastic material. Monolithic component of composite component consists of a fiber reinforced duroplastic material&#x2014;for example a composite epoxy matrix&#x2014;in which are embedded, for reinforcement, carbon fibers, basalt fibers, natural fibers, ceramic fibers, Aramide&#xae; fibers, Kevlar&#xae; fibers or any combination thereof. Monolithic component is glued to thermoplastic stiffening elements by an adhesive under the influence of pressure and temperature. Here a tolerance compensation is carried out essentially by stiffening elements, if necessary being plastically deformed, so that high dimensional stability is achieved. Composite components, which can be subject to high mechanical loads, are therefore provided, in particular, as spare or replacement parts for outer lining parts on aircraft. The invention also relates to a composite component produced by means of a method according to the invention.

Method of making a composite fibre component with thermoplastic stiffening elements

A fiber composite structural component such as a fitting, bracket, mounting or the like is produced by applying fiber material such as fiber threads or fiber yarns in an automatic circular weaving operation to a core that has at least two sections, to form a fiber material body (). One core section is removed from the fiber material body when the weaving is completed. The body is then deformed in a mold that has the contour of the finished structural component with at least one mold core section still in the fiber material body. The deformed configuration of the structural component is then impregnated in an RTM device with a resin and hardener followed by curing. Reinforcements may be inserted or secured to the fiber material body prior to the impregnated and curing step.

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Hamburg, Germany

Martin Staub