Airbus Operations Gmbh

Eads Deutschland Gmbh

Airbus Defence and Space Gmbh

Oliver Seack

Alexander Bruns

Tamas Havar

Oliver Meyer

York Caesar Roth

Tobias Ender

Hermann Benthien

Matthias Hegenbart

Markus Piesker

Juan Perez-Sanchez

Mirko Missbach

Jens Rohde

Joern Clausen

Matthias Radny

Kathrin Stubbe

Ulrich Knapp

Thomas Franke

Christian Trautmann

Sebastian Palm

A load introduction system is disclosed including an aerodynamic structure component having an upper skin section and a lower skin section, an attachment unit and a load introduction unit configured to couple the attachment unit to the aerodynamic structure component. The load introduction unit includes a longitudinal connection element with its first end positioned at the upper skin section. The longitudinal connection element extends through the lower skin section such that its second end is positioned outside of the aerodynamic structure component. The first end is anchored to the upper skin section and the second end is anchored to the attachment unit such that the longitudinal connection element forces the attachment unit against the lower skin section.

Load introduction system and a method for manufacturing a load introduction system

A load introduction system comprising an aerodynamic component and an attachment unit. The attachment unit comprises a first and a second attachment element, each of the first and the second attachment element having a mounting interface that mounts the attachment unit to a skin section and to a protrusion of the aerodynamic component. The first and the second attachment element are in contact with each other via respective contact surfaces and both attachment elements have a first opening for receiving a coupling mechanism of a base unit. The first openings coaxially align with each other and cooperatively receive the coupling mechanism. Also a method for manufacturing a load introduction system.

Load introduction system and method for manufacturing a load introduction system

A panel structure for a vehicle, and especially for an aircraft or spacecraft, includes an area member, especially a skin member, that defines an areal expanse with a first surface and an opposite second surface and having a thickness between the first and second surfaces; and a plurality of elongate stiffener members which are attached to the area member and extend over at least one of the first and second surfaces; wherein at least one of the stiffener members is bifurcated at a bifurcation point into two or more branch stiffener members.

Panel structure and associated method

An apparatus and a method for treating an object manufactured from a material having a defined melting temperature, by subjecting the object to hot isostatic pressing to reduce porosity and increase a density thereof. The method comprises arranging the object in a pressure chamber interior cavity, submerged in a liquid partially filling the cavity, heating the liquid to a below melting temperature, pressurizing the liquid by pressurizing gas above a liquid surface in the cavity, then moving the object out of the liquid, but still within the cavity, subsequently heating the liquid to an above melting temperature, and resubmerging the object in the liquid. Subsequently, the object is withdrawn from the liquid and moved above the liquid. The apparatus comprises the pressure chamber, a movable object support in the cavity, a liquid heater, and a gas inlet and outlet selectively introducing gas into and venting gas from the cavity.

Method and apparatus for treating an object

A flow body for an aircraft with a leading edge and a trailing edge includes a first spar, a second spar, and an external skin that spans from the leading edge to the trailing edge and on both sides rests on the spars. At least one of the first spar and the second spar includes a web and two spaced-apart flanges that enclose the web, on which flanges the skin that spans the respective spar is arranged. At least one of the first spar and the second spar includes at least one load introduction fin that forms an integral component with the web and extends outwards by way of one of the flanges and the skin that rests on the spars.

Flow body with a load introduction element integrated therein, method for manufacturing a flow body, and aircraft with such a flow body

A load bearing element for attachment of a heat generating unit to a heat sensitive supporting structure, wherein said load bearing element includes at least one body integrally formed by additive layer manufacturing, ALM. The body is adapted to provide a controlled heat transfer from said heat generating unit to said heat sensitive supporting structure.

Load bearing element and a method for manufacturing a load bearing element

A composite reinforcement component for an aircraft or spacecraft, including a first element assembly aligned in a first extension plane, and a second element assembly aligned in a second, perpendicular, extension plane, the second element assembly intersecting the first element assembly at an intersection of the first and second extension planes. The first and second element assembly each have a pair of staggered comb components. Each comb component includes a base and a plurality of rectangular protrusions extending coplanar from the extension planes of the respective element assembly. The rectangular protrusions form comb teeth of one comb component which are overlapping with comb teeth of the other comb component of the pairs of comb components. The comb teeth of the first element assembly are offset along the intersection by a single comb tooth width with respect to the comb teeth of the second element assembly.

Composite reinforcement component, structural element, aircraft or spacecraft and method for producing a composite reinforcement component

The present invention provides a method for producing a component for joining structures at intersection regions thereof, comprising the following steps: forming a first fiber having a meandering shape which includes a plurality of first loops; forming a second fibre having a meandering shape which includes a plurality of second loops; and swivelling a first loop portion of a respective first loop and a first loop portion of a respective second loop such that a respective first loop and a respective second loop engage with one another.

Method for producing a component for joining structures, component and structural arrangement

A lift flap bearing apparatus is improved with respect to aerodynamics, construction space and assembly, for guiding and adjusting a first lift flap and a second lift flap. The lift flap bearing apparatus comprises a first guiding device for guiding the first lift flap and a second guiding device for guiding the second lift flap. The first and the second guiding devices each have a first curved guide rail and a second curved guide rail.

Lift flap bearing apparatus, lift flap assembly, airfoil and aircraft

The present invention pertains inter alia to a method for producing a component for connecting structures at crossing regions thereof, having the following steps: depositing first and second fibers on an underlay in such a way that a respective first fiber has an offset in the longitudinal direction of the first or second fiber with respect to a respective second fiber; connecting the first and second fiber along an overlap region, in which the first and second fibers overlap; and pivoting the first and second fibers with respect to one another to form the component.

Method for producing a component for connecting structures and device

The present invention pertains inter alia to a structural arrangement, comprising a box structure, a first fibre portion which extends in a first plane, a second fibre portion which extends in a second plane, the first and the second fibre portion being interconnected at a crossing point thereof, the first fibre portion comprising a first portion on one side of the crossing point and a second portion on the other side of the crossing point, the first portion being connected to a first portion of the box structure and the second portion being connected to a second portion of the box structure, the second fibre portion forming, on one side of the crossing point, an inner web inside the box structure and, on the other side of the crossing point, an outer web outside the box structure.

Structural arrangement, aircraft or spacecraft and method

The invention relates to a method for producing a fiber composite workpiece. In the method according to the invention, cross-linking silicone is used with the aid of a volatile diluent for infiltrating individual mats of a mat composite. A further object of the present invention is a device for performing the method according to the invention.

Method for infiltrating silicone into a fiber composite structure and device for executing a method for producing a fiber composite workpiece

A component for connecting structures to intersection regions of said component is disclosed, particularly for an aircraft or spacecraft, including a coupling element, including a first fiber which wraps around the coupling element so that the first fiber extends in a first plane in front of the coupling element and in a second plane behind the coupling element, the first and second planes intersecting, and including a second fiber which wraps around the coupling element so that the second fiber extends in a third plane in front of the coupling element and in a fourth plane behind the coupling element, the third and fourth planes intersecting, and with the first fiber portions of the first and second fibers crossing over in a first region and the second fiber portions of the first and second fibers crossing over in a second region.

Component, reinforcement member, structural arrangement, aircraft or spacecraft and method

Embodiments of the invention relate to an aerodynamic body with an extension in the spanwise direction, wing chord direction and wing thickness direction for coupling to a wing of an aircraft. This aerodynamic body can here be used for a leading edge flap or slat of an aircraft wing. To improve the flow characteristics, the rear side of the aerodynamic body is provided with a skin section that can be molded between a convex curvature and concave curvature.

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Bremen, Germany

Oliver Seack