Abstract: A wing for an aircraft, comprising a main wing and a high lift assembly which includes a body, and an assembly connecting the body to the main wing, so the body is movable between a retracted position and an extended position. The assembly comprises a track extending along a longitudinal axis between first and second ends, with an intermediate portion therebetween. A roller bearing ensures that the track moves along the longitudinal axis. The roller bearing comprises bearing units, each mounted to the main wing and having a bearing surface for engaging the elongate track. The units include a first and second end units and an intermediate unit wherein, relative to the longitudinal axis, the intermediate unit is positioned between the first end unit and the second end unit. The elongate track comprises a recessed portion which, in the retracted position, aligns the intermediate unit.

Abstract: A high lift assembly (7) including: a high lift body with a high lift structure (8) and an internal volume (22), and a connection assembly (10) extending through an aperture (18) in an outer skin (20) of a leading edge of a main wing (5), the connection assembly (10) includes an elongate track (16) and a first and second connectors (12, 14), the elongate track (16) is mounted to the main wing (5) and moves along a track longitudinal axis (24), and the first and second connectors (12, 14) connect the elongate track (16), the first connector (12) is between the internal volume (22) and the outer skin (20), the second connector (14) has a longitudinal axis transverse to the leading edge of the high lift body and connects to the high lift body and the high lift structure has an opening (40) for the elongate track.

Abstract: A reinforcing device to provide an alternative improvement in the structural stability of laminated components includes a body structure having an abutment surface and at least one fastening area. The abutment surface extends along a first direction. In a cross-sectional direction, transverse to the first direction, the abutment surface includes a rounded contour section so abutment surface is configured to conform with a concave edge section of a laminated structural member. The at least one fastening area is provided at the body structure opposite to the abutment surface. The at least one fastening area is configured to secure the abutment surface against the concave edge section of the laminated structural member.

Abstract: A load introduction system comprising an aerodynamic component having a skin section with an outer surface and a first protrusion, and an attachment unit for movably coupling the aerodynamic component to a base unit. The attachment unit is attached to the skin section of the aerodynamic component and to the first protrusion, wherein the first protrusion extends away from the aerodynamic outer surface, thereby separating a space adjacent the aerodynamic outer surface into a front space and a rear space. The attachment unit extends over the first protrusion such that the attachment unit comprises a front portion in the front space and a rear portion in the rear space. Also a method for manufacturing a load introduction system.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.