Airbus Operations Gmbh

Georg Lonsdorfer

Hauke Seegel

Klaus Rode

Remo Hinz

Niels Deschauer

Adrian Wachendorf

Andreas Pau

Adam Andrä

Axel Siegfried Herrmann

Carsten Barlag

Tassilo Witte

Rolf Sundermann

Marc Fette

Thomas Meyn

Rolf-Georg Sundermann

Jens Wulfsberg

Christoph Meyer

Helmut Felderhoff

Hartmut Herter

Kevin Danke

Matthias Nothdurft

Günther Dressler

Guenther Dressler

Christian Baumgartner

Carsten Van Vuegt

A system for repairing a component made out of a plastic comprises a frame, a multiaxial guide device coupled with the frame, with a tool holder arranged thereon, an optical acquisition device, a processing device, and a plastic deposition device. The frame comprises a mounting device for retaining the frame on a component surface. The optical acquisition device, the processing device and the plastic deposition device are arranged on the tool holder. The optical acquisition device is set up to optically inspect a surface area of the component lying in proximity to the frame from at least one viewing angle, so as to acquire the spatial structure of the surface area. The processing device is set up to remove material of a damaged area from the component for generating a base surface with a desired structure and boundary edges.

System and method for repairing a component made out of a plastic

A honeycomb structure comprising carbon-fiber non-woven, sandwich structure comprising the honeycomb structure, and process for the production of the honeycomb structure.

Honeycomb structure made of a non-woven made of recycled carbon fibers

A device for the production of structural components from a fiber composite material, the components being three-dimensionally arched over a large surface, including a jig having a convex mounting surface having receiving channels for the insertion of structural components, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the mounting surface includes a plurality of individually elastically deformable mounting shell parts arranged adjacent to each other along at least one longitudinally extending pitch line and attached to a plurality of elastically deformable supporting frame elements extending on the interior of the shell at a right angle to the pitch line, and a plurality of actuators for deforming the mounting surface between an extended position (A) and at least one retracted position (B) to move the jig from the bonding device relative to the receiving channels without undercuts.

Device and method for the production of multi-arched structural components from a fiber composite

A device and to a method for the production of essentially two-dimensionally arched large-area structural components from a fiber composite material, including a jig having a convex mounting surface which has longitudinally extending receiving channels for the insertion of construction components and which can be loaded with auxiliary materials, wherein the loaded jig interacts with a laminating bonding device having a corresponding shape for forming the structural component under pressure, wherein the jig includes a mounting shell that at the edge can be elastically deformed inwards, which mounting shell, by way of a plurality of actuators that are articulated to the inside, can be moved between an extended position (A) and at least one retracted position (B) in which the jig can be moved relative to the longitudinally extending receiving channels from the laminating bonding device without undercuts.

Device and method for the production of two-dimensionally arched structural components from a fiber composite

A device for automatically laying and draping a plurality of web-form portions of a dry sheet-like formation, in particular of a multiaxial laid fiber fabric and/or a woven reinforcing fabric to create a profiled preform on a core by repeated laying and draping of the portions in order to produce a reinforcing profile with a composite material. Accordingly at least one portion, is kept in at least one cassette between two roller conveyors ready for laying on the core. As a result of the preferably simultaneous laying of preferably more than one prefabricated portion of the sheet-like formation on the core by means of at least one cassette of the cassette arrangement a profiled preform can be fully automatically laid and draped quickly and with great dimensional accuracy and at the same time with good reproducibility for the production of CRP profiles.

Method and device for laying and draping portions of a reinforcing fiber structure to produce a profiled preform

The invention relates to a production method for producing seamless, integral aircraft fuselage sections. The method comprises the following steps:

Method for producing fuselage cell sections for aircraft with composite fibre materials, and a device

A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners.

Method and a device for the manufacture of a stiffening structure for an aircraft fuselage segment, and also a stiffening structure

A method for manufacturing a fiber composite component having an integral structural design includes positioning a sheet-like fibrous semi-finished product in a mold that defines an outer contour of the fiber composite component. Dimensionally stable fibrous semi-finished products, each having dimensions corresponding to a respective portion of the manufactured fiber composite component, are arranged on the sheet-like fibrous semi-finished product. The dimensionally stable fibrous semi-finished products are stabilized and fixed in place using mold cores. The semi-finished products are resin infiltrated using one of a first or a second gating process so as to form a construct. The first gating process includes gating via the mold cores at a head of each dimensionally stable fibrous semi-finished product and performing extraction in an area of the mold. The second gating process including gating in an area of the mold and performing extraction via the mold cores at the head of each dimensionally stable fibrous semi-finished product. The construct is hardened and demolded by removing the mold cores.

Method and device for manufacturing a fiber composite component with an integral structural design

Manufacturing of a composite component, such as a composite component of an aircraft, is provided with a molding tool that includes, but is not limited to a first mold, a second mold and a pressure generator. Between the first mold and the second mold, a membrane is arranged so that between the first mold and the membrane a first region is formed, and between the second mold and the membrane a second region is formed. In the first region, a fibrous mat is arranged. In the second region with the use of the pressure generatorcounter-pressure can be produced so that the membrane is pressed in the direction of the fibrous mat.

Manufacturing a composite component

A method of manufacturing a component from a composite-fiber-material semifinished product includes providing a forming support having a contour including at least one section corresponding to a surface of the manufactured component. The semifinished product is placed onto the forming support and the semifinished product is formed such that the semifinished product contacts the forming support. Further, a device form manufacturing component includes the forming support having the contour including at least one section corresponding to the surface of the manufacture component.

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Stade, Germany

Georg Lonsdorfer