Airbus Operations Gmbh

Zf Friedrichshafen Ag

Airbus Operations (s.a.s.)

Markus Mueller

Paul Joern

Norbert Heltsch

Karim Grase

Wolf-Dietrich Dolzinski

Markus Joerg Weber

M Ichwan Zuardy

Claas De Jong

Arne Hartwig

Jens-Ulrich Prowe

Pierre C Zahlen

Axel Siegfried Herrmann

Ichwan Zuardy

Kai Borntraeger

Cihangir Sayilgan

Thomas Hoffmeister

Laurent Giuseppin

Mathias Jessrang

Sebastien Alby

Henrik Linnemann

Thomas Konsolke

Lars Fiedler

Carsten Rowedder

Matthias Jessrang

Jelle Bloemhof

A pressure bulkhead comprises a plurality of material plies arranged one above the other, wherein each material ply contains reinforcing fibers embedded in a matrix material. The reinforcing fibers, in at least one first material ply are oriented in such a manner that their longitudinal axes lie in an angle range of &#xb1;2&#xb0; about a radial direction of the pressure bulkhead.

Pressure bulkhead and method for producing a pressure bulkhead

The invention relates to a structural element for an aircraft fuselage, generally shaped in the form of a longitudinally elongate section. The element comprises two wings, each wing including: a portion that extends uninterrupted along the entire length of the section, and legs spaced apart from one another and extending from said uninterrupted portion such as to define an opening between two consecutive legs. One of the legs of one wing is arranged to face at least part of the opening defined between two consecutive legs of the other wing. Consequently, the structural element can be produced from a single fibrous preform on a curved tool, minimizing waste material and reducing the weight of said element.

Structural element for an aircraft fuselage that prevents lateral-torsional buckling

A pressure bulkhead of an aircraft with a fuselage shell and a pressure bulkhead disposed therein preferably in the rear region for forming a fuselage-internal pressure region, which pressure bulkhead is attached on the edge in the interior of the fuselage shell, wherein the pressure bulkhead has a lenticular cross-section and a sandwich construction that comprises a foam core sandwiched between two opposing exterior shells.

Pressure fuselage of an aircraft with a fuselage shell and a pressure bulkhead disposed therein

A segment and a method for producing such a segment, in particular for an aircraft, having a skin field and a skin field stiffening structure. The skin field and stiffening structure are made from fiber-reinforced plastic materials. The stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and mounts which are formed integrally with the first stiffeners and extend in a transverse direction of the first stiffeners for the connection of second stiffeners to form an integral lattice structure. Reinforcement elements are provided for mechanically fixing the mounts to the skin field. Each reinforcement element has a connection section and a blocking section having an extension in a direction inclined to the connection section. The connection section penetrates the skin field and the mounts, and the blocking section is in contact with an outer surface of the skin field.

Shell segment of an aircraft and a production method

An arrangement for attaching a system to a structure having a base element to retain the system, a positioning element to position the base element at a location on the structure and a fixation device to fix the base element at the location on the structure. The base element has a section for holding the system and a section for being clamped to the structure. The clamping section has an element for alignment on the positioning element. The positioning element has a surface for being bonded to the structure and a positioning section for acting together with the alignment element. The fixation device has a counter element with a clamping area for being positioned on an opposite side of the structure from the clamping section and a fastener for clamping the base element and the counter element to the structure. An installation method for such an attachment arrangement is provided.

Attachment arrangement and installation method

A curing tool for a shell component, includes a first tool component, which is a polyhedron and has a wedge-shaped bevel forming a first sheared edge on a first side edge, and a second tool component, which is a polyhedron, has a wedge-shaped bevel forming a second sheared edge on a first side edge and has a first corner bevel on a second side edge diagonally opposite the first side edge. The wedge angles of the first and the second sheared edge are equal.

Method for curing shell components

A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one longitudinal brace or a transverse brace is disposed so as to form at least one of longitudinal seam or a transverse seam between the double shell skin panel and the monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flanges disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the monolithic skin panel to the double shell skin panel.

Fuselage cell structure for an aircraft in hybrid design

An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft.

Aircraft structural assembly having an area element which comprises a core and an outer layer

A method of actuating a shifting element with three shift positions, having a simply controlled shifting cylinder as the actuating element, a shifting element for shifting to the three shift positions and a pressure regulator, such that the shifting cylinder is designed as a cylinder with one working line and the shifting element is pushed by the spring force of at least one spring element to an end position and moved to the other shift positions in opposition to the spring force. The central position is recognized in that, when the correct shifting element position is reached, the force for moving the shifting element in opposition to the spring force abruptly increases and, because of this, a specific pressure can be set by a pressure regulator for the central position.

Shifting element with three shift positions

A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer.

Growing community of inventors

Friedrichshafen, Germany

Markus Mueller