Airbus Operations Gmbh

Premium Aerotec Gmbh

Airbus Deutschland Gmbh

Institut Fuer Verbundwerkstoffe Gmbh

Klaus Edelmann

Tanja Frese

Angelos Miaris

Tobias Wirtz

Thorsten Roming

Tim Neitzel

Stefan Tacke

Jens Bold

Hans-Juergen Weber

Rainer Schildt

Arne Hartwig

Bengt Abel

Guenter Doehle

Timo Stöven

Guenter Hoppe

Carsten Brandt

Jens Wieting

Karsten Litzenberger

Helmut Krumpen

Timo Stoeven

Christoph Von Kopylow

Thomas Lange

Sven Sperling

Eugen Tschakrow

Klaus Hoppmann

Frank Stellberger

Matthias Schweim

Jens Wleting

Marc Bochinger

Arnoldt Quiring

Christian Weimer

Raimund Bucher

Patrick Bakker

Frank Brueggemann

Philip Hasemann

Hansjörg Horneber

Jens Bahnsen

Juergen Krone

Thorsten Schröer

Tanja Menken (Frese)

Dominik Rath

Andreas Leis

Jens Kethler

Jürgen Krone

Tanja Menken

A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that is capable of being put under internal pressure includes dome segments, having an integrated reinforcement, in particular a peripheral reinforcement, which are in each case made integrally from a fiber-reinforced thermoplastic plastics material, and are joined to one another so as to form a pressure dome.

Pressure bulkhead for an aircraft

A method for producing a thermoplastic fiber composite component, in particular for an aircraft or spacecraft, has the following method steps: material-removing processing of a first face of a first plate, wherein the first plate comprises a thermoplastic fiber composite material and a local reduction in thickness of the first plate is made by the material-removing processing of the first face; positioning a second plate relative to the first plate such that the first face of the first plate is brought into alignment with a third face of the second plate; and joining the first plate to the second plate to form a single component, wherein the surface of the first face of the first plate is integrally bonded to the surface of the third face of the second plate.

Method for producing a thermoplastic fiber composite component

A method for joining a first and a second component, at least one of which comprises a fiber-reinforced plastics material. The components are arranged in relation to one another in such a way that a gap region remains between the first and the second component. The gap region is filled, at least in portions, with an uncured plastics material filler in which nanoparticles are dispersed. Energy is introduced locally into the nanoparticles in order to cure the plastics material filler. In another aspect, the invention provides a device for joining two components.

Method and device for joining components

A semi-finished product arrangement for producing a fiber composite component by molding a planar semi-finished fiber composite product in a molding tool is provided. The arrangement includes the semi-finished fiber composite product and multiple holding elements fixed in place thereon and each extending beyond the edge of the semi-finished fiber composite product. The holding elements are countersunk in recesses of the semi-finished fiber composite product, in order to avoid a projection in terms of height.

Process for producing a fiber composite component, as well as a semi finished assembly for producing a fiber composite component

A method for edge sealing a fiber-reinforced component formed from a carbon fiber-reinforced thermoplastic or duroplastic plastic material includes electrostatic coating of at least one section of an edge of the component with a thermoplastic powder so as to form a powder coating; and fusing and cross-linking the powder coating in a furnace so as to create a smooth edge seal.

Method for edge sealing a fiber-reinforced component

A method for the manufacture of a fiber-reinforced component includes heating a blank of a carbon-fiber-reinforced thermoplastic plastic material to at least a melting temperature of the thermoplastic plastic material; introducing the blank into an at least two-part molding tool; forming the fiber-reinforced component by applying pressure on the blank using the molding tool; and injecting a further thermoplastic plastic material into at least one edge region of the molding tool so as to form an edge seal.

Method for the manufacture of a fiber-reinforced component

A non-destructive determination of material characteristics of an aircraft component is provided. To provide a simple determination of material characteristics, which can be implemented economically, it is provided to make available image data of a layer, which can be detected from outside using electromagnetic radiation, of a workpiece to be examined; to detect first areas having a first pixel characteristic using the image data; and to detect second areas having a second pixel characteristic using the image data; the first pixel characteristic being associated with a fiber inlay of a fiber composite layer; and the second pixel characteristic being associated with an at least part-crystalline thermoplastic polymer of the fiber composite layer, which thermoplastic polymer is in a crystalline state; and to determine a relationship of the first areas to the second areas.

Non-destructive determination of material characteristics

The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.

Shell segment for producing a fuselage cell section for a fuselage cell of an airplane

A method and a device for inspecting the quality of a formed thermoplastic fiber-reinforced plastic component wherein the component is tested by means of a sensor unit with a downstream electronic evaluation unit for analysis of the measuring result acquired by sensor technology by means of sample comparison, wherein by means of the optical sensor unit the surface roughness of the plastic component is measured after forming, which surface roughness is analyzed by means of the evaluation unit by a comparison with a stored reference pattern in such a manner that increased surface roughness is interpreted as increased internal materials porosity.

Method and device for inspecting the quality of a formed thermoplastic fiber-reinforced plastic component

The invention relates to a device for the production of an angle for connecting a fuselage cell skin to an annular former and/or a stringer inside a fuselage cell structure of an aircraft, the angle taking place by the one-step deformation of an initially planar blank along at least three fold lines in a uniaxial compression molding device. A mounting frame with hinges is arranged in the compression molding device, the blank to be deformed being accommodated along the edges preferably by means of a plurality of peripherally arranged springs. A deformation of the blank into an auto-stabilized angle is possible in one step while simultaneously ensuring interlaminar slide. Due to the constructively conditioned auto-stabilization of the angle, additional components which increase the weight and the assembly effort (so-called 'stabilos') in the connection region between fuselage cell skin, stringers and annular formers inside a fuselage structure of an aircraft are unnecessary.

Device for producing a component and method and component

A coupling element for connecting stringers in the process of joining two fuselage sections by means of at least one transverse splicing plate, wherein in each case the fuselage sections on the inside comprise a multitude of stringers arranged on fuselage skins, as well as annular frame elements, wherein the coupling element comprises a base flange and a frame element flange, and by way of the coupling element in each case a connection between the opposing stringers, the annular frame element and the fuselage skins or the transverse splicing plate takes place so that the coupling element beyond a connection of the stringer base also supports the connection of stringers on the flank side.

Arrangement of two fuselage sections of an aircraft and a connecting structure for connecting fuselage skins

The invention relates to a vehicle window consisting of a transparent composite material, wherein the composite material comprises fibers and a matrix material such that the vehicle window is capable of withstanding structural loads occurring in the window region and can substantially provide the window function even in spite of damage to the vehicle window (damage-tolerant), the fibers and the matrix material being transparent and substantially having the same refractive index. The invention proposes vehicle windows which are damage-tolerant, load bearing, cost-saving, easy to handle and require less installation space than conventional vehicle windows.

Load-supporting and damage-tolerant laminated aircraft window

Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The fiber laminate includes at least one full-area layer with a first fiber direction and at least one full-area layer with a second fiber direction, wherein at least one further layer with a third fiber direction is arranged in a peripheral area of the fiber laminate. This results in an orientation of the fibers in the individual layers of the fiber laminate used to reinforce the reinforcement beam that is overall suitable for the applied load, so that the reinforcement beam withstands high mechanical loads at a minimum weight.

Reinforcement beam as well as method and fiber laminate for manufacturing the reinforcement beam

The invention relates to a method for producing a component for connecting a fuselage cell skin to an annular rib of an aircraft, wherein the component is formed by bending of a flat blank along at last two edge lines and wherein the blank is formed by a CFRP. According to the invention the interlaminar sliding of the fiber layers is largely completed in a first forming step, while in a second forming step a consolidation of the component takes place by the use of pressure from the press on all sides by means of an upper tool and a lower tool. This enables complex components with at least two edge lines to be produced, which edge lines run at angles of approximately, preferably at angles of 309&#xb0; to 90&#xb0;, to each other, and which edge lines also lie in at least two different planes.

Process for the production of a component, and fibre-reinforced thermoplastic component

A closed ring fiber reinforced frame structure is produced by first preparing a prepreg. A section of the prepreg is formed into a flange preferably after impregnation by folding the flange section along a folding line. The folding line is formed by securing a deformable or drapable fiber ribbon material, for example by sewing or stitching to a carrier substrate which is preferably also a fiber material. The sewing seam or stitching line becomes the folding line. The ribbon material is so secured to the carrier substrate that the fiber orientation of the ribbon material is uniformly distributed all around a ring component that is formed of the ribbon material on the substrate. The impregnated ring component with its substrate is then cured after the folding of the flange to complete the ring frame structure.

Method for producing a three-dimensional fiber reinforced ring frame component

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Bremen, Germany

Klaus Edelmann