Eads Deutschland Gmbh

Airbus Operations Gmbh

Daimler Chrysler Ag

Airbus Defence and Space Gmbh

Franz Stadler

Stefan Utecht

Julian Kuntz

Tamas Havar

Xavier Hue

Thomas Lippert

Marco Goettinger

Torsten Lorenz

Hans-Wolfgang Schröder

Hans-Wolfgang Schroeder

Kay Dittrich

Ulrich Prechtel

Thomas Koerwien

Thomas Körwien

Olaf Rocker

Michael Sabielny

Jochen Scholler

Herbert Zippold

Wilhelm Wulbrand

Bernhard Schönlinner

Bernhard Schoenlinner

Thomas Schuster

Jürgen Filsinger

Markus Rothenhaeusler

Kay W Dittrich

Markus Rothenhäusler

Patrick Ter

Peter Müller-Hummel

Gerd Berchthold

A method for producing a load introducing element for a control surface of an aircraft or a spacecraft, includes cutting to size preformed fibrous substructures out of a fibrous material. The method also includes draping the fibrous substructures to mold at least one first component, at least one second component and at least one first flange in the form of a single semi-finished product. Further, the method includes inserting the semi-finished product into a mold, injecting matrix material, and curing the semi-finished product to form a finished product.

Method for producing a load introducing element

A device for shaping a workpiece is provided. The device includes at least one first and one second component between which the workpiece to be shaped can be molded under the effect of heat. The design and/or the material properties of the first and/or the second component are selected such that the component's thermal expansion is different in different directions.

Device for shaping a workpiece

A method is provided for manufacturing a radome. The method has the following steps: creation of a contoured fit of at least one section of an inner surface of a wall of the radome; arrangement of a plurality of planar photosensitive semiconductor elements on an outer surface of the contoured fit; placement of the contoured fit with the plurality of planar photosensitive semiconductor elements on the at least one section of the inner surface of the wall; establishing of a connection between the plurality of planar photosensitive semiconductor elements and the wall; and removal of the contoured fit from the radome. This method enables the simple manufacture of a radome with a layer having several semiconductor elements for the electromagnetic shielding of the interior of the radome.

Method for manufacturing a radome

A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.

Load introducing element

A method for preforming a textile semi-finished product, including arranging a textile having at least two layers of fibers, interwoven fibers and/or fiber bundles that are at least in part arranged on top of each other. The method also includes; fixing-in-position of the fibers of the textile against each other and then cutting-to-size of the textile. The fixing-in-position of the textile involves irradiating via a laser beam in order for the melt-on binder of the textile to be melted on only in a localized fashion and not evaporated. The fixing-in-position occurs along a fix-in-position line, the cutting-to-size occurs along a cut-to-size line, and the fix-in-position line is located at a distance relative to the cut-to-size line that is so small that any fraying of the textile is reduced or suppressed altogether.

Method for pre-forming a textile semi-finished product and a pre-forming apparatus

Injection structure with a fiber-composite semifinished product for manufacturing a fiber-composite component, having a gate device for feeding matrix material, a distribution fabric, and a barrier layer that is impermeable to the matrix material, wherein the distribution fabric is arranged between the gate device and the fiber-composite semifinished product, and the barrier layer is arranged between the distribution fabric and the fiber-composite semifinished product, as well as device for manufacturing a fiber-composite component by this injection structure.

Method and devices for producing fiber-reinforced components

Production device and method for producing fiber-reinforced plastic components comprising a semi-finished prepreg product and a dry semi-finished textile product with an aeration and deaeration chamber and an exhaust line opening into the same for producing a vacuum and a semi-finished textile product chamber to receive a dry semi-finished textile product. Into the semi-finished textile product chamber an injection line for inserting resin opens, whereby a prepreg chamber for receiving a semi-finished prepreg product is provided. The prepreg chamber is located against the aeration and deaeration chamber in an air-permeable manner and the semi-finished textile product chamber is located against it at least in areas in an air-impermeable and resin-permeable manner. Due to the air-permeable membranes, a vacuum in the aeration and deaeration chamber generates a vacuum both in the prepreg chamber and in the semi-finished textile product chamber. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Method and device for producing fiber-reinforced plastic components

Degassing device for degassing matrix material in the manufacture of fiber-composite components with a support device, a distribution fabric, a gate device, a discharge device, a matrix-material-impermeable barrier layer, which is sealed with respect to the support device by a seal and thus forms a first chamber of the degassing device located around the gate device, as well as a degassing device for degassing matrix material in the manufacture of fiber-composite components with a first connection, for conducting the matrix material to be degassed into the degassing device, a second connection for conducting the degassed fluid out of the same, and a third connection for applying negative pressure to the interior of the same, an inner body, a resin-impermeable and air-permeable film, and an outer housing.

Degassing device for degassing matrix material in order to produce fiber-reinforced components

In a method for producing fiber-reinforced plastic components made of dry fiber composite preforms by an injection method for injecting matrix material, the arrangement of the fiber composite preform on one surface of the preform resulting in a flow promoting device, on a tool, creates a first space by a gas-permeable and matrix-material-impermeable membrane surrounding the preforms. Formation of a second space arranged between the first space and the surroundings by a foil, which is impermeable to gaseous material and matrix material, is provided, with removal by suction, of air from the second space resulting in matrix material being sucked from a reservoir into the evacuated first space and with the flow promoting device causing distribution of the matrix material above the surface of the preform facing the flow promoting device, thus causing the matrix material to penetrate the preform vertically.

Method and device for producing fiber-reinforced components using an injection method

A method for producing a fibre-reinforced plastic component includes (1) prefabricating an unwindable part of the plastic component as a prepreg semi-finished material; (2) prefabricating a non-unwindable part of the plastic component as a textile semi-finished material; (3) applying a resin film to said textile semi-finished material; (4) joining said textile semi-finished material and said prepreg semi-finished material in a curing device; (5) evacuating said curing device; and (6) subjecting said curing device to temperature and pressure treatment in an autoclave.

Method for producing fibre-reinforced plastic components

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Boehmfeld, Germany

Franz Stadler