Abstract: A high-lift system for an aircraft includes a high-lift flap which is arranged on the wing of the aircraft and is mounted on a carriage coupled to the wing, the carriage being displaceably mounted on a track by means of a high-lift bearing. The high-lift bearing includes a plain bearing.

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 method for producing a load introducing element for a control surface of an aircraft or a spacecraft, includes cutting to size preformed fibrous substructures out of a fibrous material. The method also includes draping the fibrous substructures to mold at least one first component, at least one second component and at least one first flange in the form of a single semi-finished product. Further, the method includes inserting the semi-finished product into a mold, injecting matrix material, and curing the semi-finished product to form a finished product.

Abstract: A load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in.

Abstract: A load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in.

Abstract: The invention relates to a connection arrangement for connecting two profiled elements in a seamless and aerodynamically smooth manner in order to form a profiled surface around which a laminar flow is possible. A first profiled element has a first fixing strip that extends towards the second profiled element, and the surface of the first fixing strip is lower than the surfaces of the profiled elements in the outward direction. Furthermore, the second profiled element has a second fixing strip which is molded on the inside and which is arranged below the first fixing strip, and the two profiled elements are rigidly connected to each other by means of the second fixing strip. A filler region that can be found below the connecting surface between the profiled surfaces and above the fixing strip surface is tilled with at least two layers of cured filling material. A method for filling the filling region with filling material and a device for carrying out the method are also claimed.

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: A high-lift system for an aircraft includes a high-lift flap which is arranged on the wing of the aircraft and is mounted on a carriage coupled to the wing, the carriage being displaceably mounted on a track by means of a high-lift bearing. The high-lift bearing includes a plain bearing.

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 load-bearing fairing element for a flap adjustment mechanism of an aircraft comprises a shell-shaped fairing housing with an at least partly U-shaped profile with an open side, a closed side, and a direction of main extension, at least one first cover panel that along the direction of main extension covers part of the open side, and a load-bearing bridge element. The bridge element is arranged in the fairing housing and with a base area conforms so as to be flush against an internal surface of the fairing housing and extends towards the open side. The bridge element comprises an essentially planar cover area that covers the base area on the open side in order to produce a closed profile contour that is circumferential on the direction of main extension. The bridge element comprises means for holding a shaft feed-in of a central flap drive and means for holding an adjustment mechanism that is couplable to the shaft feed-in.

Abstract: A method for producing a load introducing element for a control surface of an aircraft or a spacecraft, includes cutting to size preformed fibrous substructures out of a fibrous material. The method also includes draping the fibrous substructures to mold at least one first component, at least one second component and at least one first flange in the form of a single semi-finished product. Further, the method includes inserting the semi-finished product into a mold, injecting matrix material, and curing said semi-finished product to form a finished product.

Abstract: A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.

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 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.

Abstract: The invention relates to a connection arrangement (30b) for connecting two profiled elements (32, 34) in a seamless and aerodynamically smooth manner in order to form a profiled surface around which a laminar flow is possible. A first profiled element (32) has a first fixing strip that extends towards the second profiled element (34), and the surface (44) of the first fixing strip is lower than the surfaces of the profiled elements (32, 34) in the outward direction. Furthermore, the second profiled element (34) has a second fixing strip (44) which is molded on the inside and which is arranged below the first fixing strip (36), and the two profiled elements (32, 34) are rigidly connected to each other by means of the second fixing strip. A filler region that can be found below the connecting surface (55) between the profiled surfaces (32, 34) and above the fixing strip surface (44) is tilled with at least two layers of cured filling material.

Abstract: 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.

Abstract: 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.

Abstract: A fiber composite component is at least partially produced by braiding. It comprises a core element which has at least one concavely constructed face that is adjoined by a passage opening. Respective opposite transverse or longitudinal sides of the core element and the side of the passage opening not bounded by the core element are enclosed by a braided fiber composite loop element.

Abstract: A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.

Abstract: A fiber composite component is at least partially produced by braiding. It comprises a core element which has at least one concavely constructed face that is adjoined by a passage opening. Respective opposite transverse or longitudinal sides of the core element and the side of the passage opening not bounded by the core element are enclosed by a braided fiber composite loop element.