Airbus Operations Gmbh

Manuel Jung

Michael Bechtold

Olaf Rocker

Thorsten Bleck

A method for manufacturing a multilayer fiber structure includes providing a receiving surface being formed by a first surface region of a contoured tool surface of a forming tool component and a support surface of a support component. Further, at least one fiber layer is formed on the receiving surface by laying down a plurality of fiber tapes onto the receiving surface. A roller device is positioned so as to press the at least one fiber layer against the tool surface and the support component and the roller device are synchronously moved along a curved transition region connects the first surface region to a second surface region of the tool surface. Thereby the at least one fiber layer is abutted against the transition region and the second surface region of the tool surface. Further, a tool system for manufacturing a multilayer fiber structure is disclosed.

Method and tool system for manufacturing a multilayer fiber structure

A fiber composite component having a first and a second fiber composite element each bent along a transverse axis opf the fiber composite component to have, respectively, in succession, a first and second base flange, a first and second web section, a first and second top flange and a first and second stiffening web. Respectively, the first and second base flanges are parallel to the first and second top flanges, the first and second web sections are angled with respect to each of the first and second base flanges and the first and second top flanges, the first and second stiffening webs are at right angles with respect to the first and second top flanges, and the first stiffening web and the second stiffening web are congruent with respect to one another, and are connected to one another, along a longitudinal axis of the fiber composite component.

Fibre composite component and method for the production thereof, and wing structure

In a method for manufacturing components from composite fiber materials, at least one placeholder is inserted into a recess in a molding tool, wherein the unfinished component is subsequently produced, the placeholder is removed, at least one lifting pad is inserted into the recess and the unfinished component is removed from the molding tool by inflating the lifting pad. In a system for manufacturing components from composite fiber materials, the component removal process is monitored and controlled by a computer unit in order to prevent predetermined maximum component loads from being exceeded. The gentle component removal process makes it possible to avoid consequential costs for repairing or reworking the components.

Method, system and molding tool for manufacturing components from composite fiber materials

The invention provides a method for producing a component () for aerospace, with the following method steps: supplying a lay-up arrangement () to be laid by means of a tape-laying machine (), with a glass-fiber lay-up (), which is preimpregnated with a resin matrix (), and/or supplying a structural arrangement () to be laid by means of a tape-laying machine (), with a structure () which is made of metal and is preimpregnated with a resin matrix (), laying the lay-up and/or structural arrangement () on a laminating apparatus () by means of a tape-laying machine (), and curing the lay-up and/or structural arrangement () and therefore forming the component ().

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Hamburg, Germany

Manuel Jung