Airbus Operations Gmbh

Airbus (sas)

Tassilo Witte

Pierre C Zahlen

Alexei Vichniakov

Hauke Seegel

Alois Friedberger

Axel Siegfried Herrmann

Philippe Blot

Alexander Gillessen

Andreas Helwig

Georg Lonsdorfer

Wolfgang Machunze

Christian Thomas

Mohamed-Mourad Sayeh

Jan Huelnhagen

Thomas Hoffmeister

Niels Deschauer

York Caesar Roth

Alexander Engels

Rolf Sundermann

Jan Schoppmeier

Adam Andrä

Julian Kupski

Elmar Bonaccurso

Rene-Philipp Jaekel

Hannes Winter

Jons Velten

Adam Andrae

Johann-Christian Koerbelin

Rene-Philipp Jäkel

Jan Hülnhagen

Jens Walla

Fabian Eling

Bernd Otte

Johann-Christian Körbelin

Jan Kako

A method for joining two components of a meltable material comprises the steps of providing a first component having a first border region and a second component having a second border region, placing the second component relative to the first component so as to form an overlap between the first border region and the second border region under a gap between the first border region and the second border region, continuously heating opposed sections of the first border region and the second border region at the same time through at least one energy source arranged in the gap at least partially, continuously providing a relative motion of the at least one energy source along the first border region and the second border region in the gap, and continuously pressing already heated sections of the first border region and the second border region onto each other.

Method and system for joining two components of a meltable material

An assembly, configured in particular in the form of an aircraft assembly, comprises a plurality of individual components composed of a fibre-reinforced composite material. An edge section of at least one individual component is sealed by means of a sealing tape which contains reinforcing fibres and a curable plastics material.

Assembly having individual components made of a fibre-reinforced composite material

For forming profile elements, in particular trapezoidal or &#x3a9;-shaped profile elements, from a multilayer stacking of pre-impregnated fibers, the stacking is moved in feed direction with feed speed by sets of conveyor belts which engage with the upper and lower surfaces of the lateral edge sections of the stacking and hold the edge sections in a starting plane. The sets of conveyor belts are arranged so that the distance between the sets engaging with opposite edge sections decreases in feed direction. To conduct the forming step a middle portion of the stacking is moved over a ramp upwardly inclined in feed direction with respect to the starting plane.

Method and an apparatus for forming profile elements

A system and method for producing a composite component, especially for continuous production of such composite components, includes a feeding device for feeding one or more layers of reinforcing material from a material supply along a process path, a resin application device for applying a resin matrix to the reinforcing material fed along the process path, and a forming device configured to shape or mould a profile of the reinforcing material and the resin matrix applied thereto to form a composite component as the reinforcing material is fed or conveyed along the process path.

System and method for producing composite component

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 support mandrel for producing curved composite components includes a prismatoid mandrel body formed from a flexible material, the mandrel body having two polygonal bases and an upper support surface extending between the two polygonal bases of the mandrel body, and a reinforcement bar enclosed within the mandrel body and extending between the two polygonal bases of the mandrel body substantially parallel and near to the upper support surface of the mandrel body.

Support mandrel, method and system for producing curved composite components

A method for producing a textile preform includes manufacturing a multi-layer fiber fabric, which includes a first flange portion and a web portion connected to the first flange portion, deforming a first fiber layer of the first flange portion with respect to the web portion, such that the first fiber layer is at a first flange portion angle to the web portion, a web height of the web portion being set in a variable manner during the deformation of the first fiber layer, and depositing a unidirectional fiber fabric only on the deformed first fiber layer of the first flange portion.

Method and device for producing a textile preform

A process for the recycling of wastes from webs or strands made of prepreg wastes comprising a first reactive resin, having the following steps: homogenization of prepreg wastes, dispersion of fillers and/or additives in a second reactive resin, mixing of the second resin, homogenized prepreg wastes and further processing of the mixture of resin, fillers and/or additives and prepreg wastes to produce molded workpieces.

Process for the production of press compounds (BMC) from unhardened prepreg wastes

A system is provided for producing components of composite material, and especially elongate or continuous components of fiber-reinforced polymer. The system comprises a winding mechanism for winding an elongate sheet of composite material about a winding axis that is at an angle to a perpendicular to a longitudinal axis of the elongate sheet so as to form a helical coil of wound sheet a mechanism is provided for drawing or conveying the helical coil of wound sheet along a process path, wherein the process path is preferably substantially parallel to the winding axis. A shaping mechanism forms or shapes the coil of wound sheet as it is drawn or conveyed along the process path. A corresponding method of producing a composite component is provided.

Method and system for producing composite component

A method of repairing an affected area of a component of a fiber-reinforced polymer composite, especially having elongate or continuous reinforcing fibers in a polymer matrix, is disclosed. The method includes: providing a controlled atmosphere around the affected area of the component; heating the component in the affected area within the controlled atmosphere to cause pyrolysis or depolymerization of the polymer matrix in the affected area and thereby to remove the polymer matrix from the affected area; introducing polymer resin into a space left by the pyrolyzed or depolymerized matrix to refill the affected area.

Method and apparatus for repairing composite components

The present invention relates to a method of forming a curved prepreg strip or sheet, especially for use in fabricating a composite component. The method includes providing a strip or sheet of prepreg material having reinforcing fibers and drawing or conveying the prepreg material in a travel direction, wherein the material is drawn or conveyed in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction. Similarly, the invention relates to an apparatus for forming a curved prepreg strip or sheet, having: a mechanism for drawing or conveying a strip or sheet of prepreg material in a travel direction, wherein the mechanism is configured to draw or convey the strip or sheet of prepreg material in the travel direction at a speed which differs across a width of the strip or sheet transverse to the travel direction.

Method and apparatus for forming a curved prepreg strip

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

A method of producing a composite preform having a profile with variable profile height or width is provided. The method includes: providing a plurality of first fiber layers overlapping or upon one another in or substantially parallel to a primary plane; inserting a second fiber layer via a guide member between two of the first fiber layers at an edge region of the preform profile, such that the second fiber layer extends substantially parallel to the first fiber layers; and positioning the edge region of the preform profile, and thus respective edge regions of the first fiber layers, out of the primary plane to set or determine a dimension of the preform profile in the primary plane.

Method for production of composite preform

Method for manufacturing a dry textile preform, including: pulling a textile fabric sheet; grabbing a first side portion of the sheet between rollers, the rollers forming a first flange of the first side portion of the sheet inclined at a predeterminable angle to the plane of extension of the sheet; grabbing a second side portion of the sheet opposite to the first side portion between other rollers, the other rollers forming a second flange of the second side portion of the sheet inclined at a predeterminable angle to the plane of extension of the sheet; adjusting a difference between the rolling speed of the pair of first rollers and the rolling speed of the pair of second rollers to form a curvature radius of the sheet; and adjusting distance between the rollers perpendicular to the movement direction of the sheet to form a web portion between the first flange.

Growing community of inventors

Hamburg, Germany

Tassilo Witte