Airbus Operations Gmbh

Wolfgang Eilken

Memis Tiryaki

Wolfgang Schulze

Bruno Stefes

Matthias Hegenbart

Sven Werner

Erich Paul

Andre Zybala

Torsten Noebel

André Zybala

Michael Sauer

Magdalena Boyen

Stefan Tacke

Karim Grase

Dirk Elbracht

Marc Schimmler

Jens Telgkamp

Dimitri Orlov

Christian Bartels

Sven Hardy Werner

Anton Arosenko

Klaus-Peter Sanmann

Henning Felgenhauer

Lena Duken

Stefan Brunner

Dirk Richter

Ralf Reinhold

Daniel Sauer

Simone Ruether

Ghasem Moussavi

Patrick Brusberg

Christoph Schweim

Marcus Bolbrinker

A rail for the fastening of equipment elements, such as, in particular, seats, in aircraft, includes a holding region for connection to an equipment element of an aircraft, and a support region to fasten the rail to a carrier element of the aircraft. The rail has a metallic shell which is, for example, made of titanium and which is filled with a fiber-reinforced thermoplastic filler material which is reinforced by short fibers. To produce the rail, a metallic molded part is used as a casting mold and is filled, for example by injection, with the filler material and, after the rail has been produced, forms the metallic shell for the filler material.

Rail for the fastening of equipment elements in aircraft, in particular seats, and method for production

A shell arrangement for a fuselage of an aircraft includes a first shell portion extending in a curved manner in a shell peripheral direction and a second shell portion extending in a curved manner in the shell peripheral direction, wherein, in an overlapping portion of the shell arrangement, a first end region of the first shell portion and a second end region of the second shell portion overlap each other in the shell peripheral direction and a first outer face of the first shell portion and a second inner face of the second shell portion are adhesively bonded to each other by an adhesive layer, and wherein an edge of the first shell portion which terminates the first end region with respect to the shell peripheral direction extends in the overlapping portion in an undulating manner in a shell longitudinal direction which extends transversely relative to the shell peripheral direction.

Shell arrangement for a fuselage of an aircraft and fuselage for an aircraft

A method for producing a crossmember for a vehicle prepares a workpiece having different thicknesses and a preliminary contour from a metal sheet of uniform thickness by flat roll forming to achieve different local thicknesses. The method cuts out the workpiece, and bending roll forms the workpiece to form a crossmember with a cross section having at least two flanges opposite one another, and a web situated between said flanges. The distance between the flanges is not constant along a longitudinal extent of the crossmember, and a thickness profile at least of the web is determined by the flat roll forming. The local thicknesses and the preliminary contour are such that a geometrical shape of the crossmember corresponds to a predetermined geometrical shape with different thicknesses and heights of the web and differently shaped regions of the flanges along the longitudinal extent of the crossmember.

Method for producing a crossmember for a vehicle and a crossmember for a vehicle

A floor system for creating a floor in an interior of a vehicle has base part and a floor panel. The base part having a trough-shaped depression and the floor panel are attached to a floor support structure and together provide a customary installation height and also cavities for accommodating installation objects.

Floor system for a vehicle

A fairing for an aircraft is disclosed in which the fairing comprises a first fairing portion configured to be fixedly attached to a first structural component and having a first edge; a second fairing portion configured to be fixedly attached to a second structural component and having a second edge, wherein the first edge and the second edge define an interface configured to enable relative movement between the first fairing portion and the second fairing portion.

Fairing for an aircraft

A rail system for fixing fittings in a cabin of a vehicle includes a first elongate rail body with a fixing side for fixing to a vehicle structure, an opposite support side with a support surface for receiving fittings, and a rail cross-section extending between the fixing side and the support side, and several fixing inserts which can be fixed along the support surface. The rail cross-section has two mutually opposing legs which are spaced apart from each other and run perpendicularly to the support surface, and the fixing inserts are configured so as not to protrude beyond the support surface.

Rail systems for fixing fittings in a cabin of a vehicle

A pressure bulkhead system comprises a pressure bulkhead adapted to be connected to a fuselage of a vehicle to separate a pressurized cabin space of the vehicle from an unpressurized cabin space of the vehicle, and a peripheral pressure frame to sealingly connect the pressure bulkhead to the vehicle fuselage. The peripheral pressure frame comprises an attachment section sealingly attached to an outer rim portion of a first surface of the pressure bulkhead. The first surface, when the pressure bulkhead system is installed in the vehicle, faces the unpressurized cabin space of the vehicle. A flange section is adapted to be sealingly attached to an inner surface of the vehicle fuselage and extends in a direction facing away from the first surface of the pressure bulkhead. A flexible section interconnects the attachment section and the flange section and is flexible to accommodate cabin pressure acting on the pressure bulkhead.

Pressure bulkhead system

A fuselage section of an aircraft has an inner surface with a non-circular contour. A pressure bulkhead for use in the fuselage section has a non-circular outer edge that is aligned with the non-circular contour of the inner surface of the fuselage section. The pressure bulkhead has a spherically-shaped inner section having radially arranged stiffening units and a non-spherically outer section having additional radially arranged stiffening units; the stiffening units corresponding to each section do no extend into the other section. The pressure bulkhead is attached to the fuselage section. A method of manufacturing a fuselage section having such a pressure bulkhead is also provided.

Pressure bulkhead adapted to non-circular fuselage section

A vortex generator arrangement for an aircraft, a flow control system and an aircraft comprising such vortex generator arrangement. The arrangement includes a surface portion facing a first region of space to constitute a flow surface, a vortex generating element, an element support structure connected to the element, a mounting structure. The element support structure and the element together are rotatable between first and second positions and a biasing device, retainer and release are provided. The rotational axis extends transversely with respect to the surface portion. The projection of the element onto a projection plane is smaller in the first rotational position than in the second rotational position, the projection plane extending perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to the extension of the tangent plane.

Vortex generator arrangement for an aircraft

A fuselage structure includes a pressure bulkhead and a frame being arranged behind the pressure bulkhead. The fuselage structure includes a first beam element with a first cantilever and a second cantilever, while the first beam element extends in a vertical direction of the fuselage structure. The first cantilever and the second cantilever protrude from the first beam element in a first direction toward the frame. The first direction of both cantilevers is inclined at a first angle with respect to a longitudinal direction of the fuselage structure. An aircraft with a fuselage structure and a method for manufacturing a fuselage structure are also described.

Fuselage structure and method for manufacturing a fuselage structure

A vertical stabilizer for an aircraft, including a fin, pivotable rudder, rudder adjustment arrangement, and vortex generator arrangement having on each side of the fin a turbulence generation element, each turbulence generation element disposed in a surface section of the fin and mounted moveably between a first, retracted position, where it is retracted into an interior space of the fin, and a second, extended position, where it projects at least partially outwardly from the fin transversely with respect to the surface section, and a turbulence generation element adjustment arrangement which is coupled to the rudder. The turbulence generation element adjustment arrangement engages the turbulence generation elements to move them. In a range of angular positions of the rudder, the turbulence generation element adjustment arrangement is inoperative for causing a movement of the turbulence generation elements out of the first position.

Vertical stabilizer for an aircraft

Inter alia, an apparatus including a ramp, the ramp configured to enable variation of a cross section of a ram air passage of the apparatus. The ramp includes a first rigid member, a second rigid member and a flexible member coupled to the first rigid member and the second rigid member. The ramp is movably mounted at two ends. Moreover, a method of varying the cross section of the ram air passage of such an apparatus by moving the ramp of the apparatus is disclosed. Further, an arrangement including such an apparatus and a ram air channel communicating with the ram air passage is disclosed.

Varying a cross section of a ram air passage

A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.

Vortex generator arrangement, flow control system and method for controlling a flow on a rudder surface

A method for adapting a 3D printing model includes calculating a layer representation model on the basis of a 3D object model of an object; determining a plurality of overhang regions in the layer representation model where the boundary edges of first layers extend over the boundary edges of second layers, the first layers being directly adjacent and subsequent to the second layers when going into the build-up direction of the layer representation model; determining a local overhang angle in each of the plurality of overhang regions; adapting the layer representation model by re-defining the boundary edges of layers in the overhang regions so that the local overhang angle remains below a predetermined overhang threshold angle; and outputting the adapted layer representation model as 3D printing model to the 3D printing apparatus.

Growing community of inventors

Hamburg, Germany

Wolfgang Eilken