Airbus Operations Gmbh

Fraunhofer-gesellschaft Zur Foerderung Der Angewandten Forschung E.v.

Fft Produktionssysteme Gmbh & Co. Kg

Alexander Engels

Joachim Piepenbrock

Pierre C Zahlen

Tassilo Witte

Thomas Hoffmeister

Lars Meyer

Gregor Graßl

Klaus Apel

Karsten Gensicke

A system for handling a first component includes: a main-device and a module-device, the module-device having a pressing section arranged to form an outer surface of the module-device, the module-device configured to releasably receive the first component, such that a connection section of the first component is attachable to the pressing section of the module-device. The module-device is releasably connected to a second component, wherein the main-device includes a grabbing unit adapted for releasably connecting the module-device, such that the pressing section is arranged to form a first outer surface section of the main-device, and wherein the main-device includes a connector for connecting to a handling-unit for arranging the main-device at the second component, such that the connection section of the first component, if attached to the pressing section of the module-device, is at least indirectly attachable to a front surface of the second component.

System and method for handling a component

A method for producing a smooth aerodynamic surface of an aircraft component is depicted and described. The method includes: provision of an aircraft component with an aerodynamic surface, which has an uneven section, introduction of a liquid or viscous, uncured sealing compound into the uneven section, introduction of a solid, precured sealing body into the uneven section in such a way that the sealing body presses into the sealing compound until the sealing compound at least partially surrounds the sealing body, curing of the sealing compound.

Method for producing a smooth aerodynamic surface of an aircraft component

A system for producing a fiber-reinforced composite module, such as a panel module, having an integrated stiffening structure for an aircraft or spacecraft includes a form core assembly station for assembling a plurality of form cores covered with reinforcing fiber layers to constitute at least one stiffening element of the integrated stiffening structure, a form core placement station which receives assembled form cores from the assembly station for placing or depositing the assembled form cores in or on a molding tool, and a turning station for rotating or inverting the assembled form cores. The turning station is configured to convey or transport the assembled form cores from the assembly station to the placement station. The turning station defines a path which is configured to rotate or invert the assembled form cores as they are conveyed or moved to the placement station.

System and method of manufacturing composite modules

Disclosed is a method and an apparatus for extracting a long fiber, and in particular an endless fiber, embedded in a resin matrix forming a wound composite part, wherein the fiber is extracted as one single part by unwinding after a pyrolisis treatment for a decomposition of the matrix.

Method and apparatus for extracting a fiber of a wound composite part

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Hamburg, Germany

Alexander Engels