Abstract: A method for manufacturing a stiffened aerodynamic structure component includes: providing an aerodynamic structure component, wherein the aerodynamic structure component includes a plurality of spar elements extending spanwise within the aerodynamic structure component; wherein the plurality of spar elements is integrally formed with an upper skin section and a lower skin section, thereby providing an integrally formed aerodynamic structure component, and generating at least one chordwise reinforcement element by injecting a curable medium, preferably via at least one injection hole, in the upper skin section and/or the lower skin section.

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 kinematics assembly for a high lift body, in particular a droop nose or leading-edge-slat, configured to be mounted to a main body of a wing of an aircraft, a corresponding support station for supporting the high lift body, and a high lift body arrangement includes an actuation organ providing a drive mounting point configured to mount the kinematics assembly to a drive organ for moving the high lift body with respect to the main body between a stowed position and a deployed position, and a deflection organ configured to be connected to the actuation organ and providing a central hinge point for hinging the high lift body at the main body movably between the stowed position and the deployed position; wherein, at least in the stowed position, the drive mounting point is located aft of the central hinge point with respect to a travel direction of the aircraft.

Abstract: A heated leading edge structure (14) for an aircraft (10) including a leading edge panel (20) having an outer surface (32) configured to contact an ambient flow (A), and an inner surface (34) opposite the outer surface (32); a reinforcing member (22) connected to the inner surface (34) of the leading edge panel (20), and a heating arrangement (24) configured to heat the leading edge panel (20); wherein the heating arrangement (24) includes an indirect heating device (44) mounted on the reinforcing member (22) and configured to heat the leading edge panel (20) by conduction through the reinforcing member (22).

Abstract: An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper skin panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.

Abstract: A vortex generating system with a vortex generator formed by a base, a baffle, moveable in rotation around a rotation axis relative to the base, and an actuator, configured to move the baffle in rotation around the rotation axis relative to the base. A control unit is connected to the vortex generator. The control unit has an acquisition module configured for acquiring a target active position of the baffle, a control module configured for controlling the actuator into an active configuration, in which the actuator is applying a controlling torque to the baffle depending on the acquired target active position, and an evaluation module, configured for generating an inconsistency evaluation signal as a function of the controlling torque and of the target active position.

Abstract: A vortex generator for an aircraft. The generator includes a base configured to be connected to an external surface of an aircraft, a baffle being connected to the base and moveable in rotation around a rotation axis relative to the base, and an actuator configured to move the baffle in rotation around the rotation axis relative to the base. The actuator is controllable into at least one active configuration in which the actuator is moving the baffle to a predetermined active position relative to the base and a passive configuration, in which the actuator is allowing rotation of the baffle relative to the base. The baffle is in a feathered position relative to the base when the actuator is in its passive configuration.

Abstract: A drive system for a lift control device of an aircraft. The drive system has first and second connection assemblies. The first connection assembly comprises a first track comprising a first end coupled to the lift control device and a track curvature having a radius of curvature; a first guiding element to absorb side loads from the first track; a first drive device to drive the first track, and a second guiding element to sense spanwise movement of the first track. The second connection assembly comprises a second track comprising a first end coupled to the lift control device; a third guiding element to absorb side loads from the second track, and a second drive device to drive the second track. The first and second drives are mechanically coupled by a transmission shaft. When the spanwise movement exceeds a threshold value, the drive system is stopped.

Abstract: A forward fairing for an aircraft. The forward fairing includes a fairing shell and an attachment member. The attachment member includes a protrusion that is integrally formed with the fairing shell and a spigot that is coupled to the protrusion. Also, an aircraft structure with such a fairing, a flap support structure with such a fairing, and an aircraft with such a fairing.

Abstract: A fairing for an aircraft, comprises a wall element comprising an inner surface and an outer surface, wherein the outer surface is exposed to a free air flow outside the fairing, and at least one stiffener element attached to the inner surface of the wall element, to keep the fairing in shape under dynamic pressure loads. The fairing comprises at least one air inlet device comprising an inlet opening for a part of the free air flow outside the fairing to pass through the wall element and to enter the interior of the fairing. The air inlet device is at least partially integrated into the stiffener element, and the inlet opening of the air inlet device is formed in the stiffener element and extends into or through the stiffener element. The air inlet device and the stiffener element may be integrally formed as a single part, by 3D printing.

Abstract: An aerodynamic system for an aircraft. The aerodynamic system includes a first aerodynamic component configured to be movably coupled to a primary structure of the aircraft, a second aerodynamic component which is movably coupled to the first aerodynamic component and a first panel element coupled to the first aerodynamic component. The first panel element at least partially covers a gap between the first aerodynamic component and the second aerodynamic component. The aerodynamic system further includes a sealing element arranged between the first aerodynamic component and the second aerodynamic component. The sealing element is configured to at least partially block an airflow between the first aerodynamic component and the second aerodynamic component.

Abstract: A drive system for a lift control device of an aircraft. The drive system has first and second connection assemblies. The first connection assembly comprises a first track comprising a first end coupled to the lift control device and a track curvature having a radius of curvature; a first guiding element to absorb side loads from the first track; a first drive device to drive the first track, and a second guiding element to sense spanwise movement of the first track. The second connection assembly comprises a second track comprising a first end coupled to the lift control device; a third guiding element to absorb side loads from the second track, and a second drive device to drive the second track. The first and second drives are mechanically coupled by a transmission shaft. When the spanwise movement exceeds a threshold value, the drive system is stopped.

Abstract: A wing for an aircraft has a main wing and a trailing edge high lift assembly which has a flap and a connection assembly movably mounting the flap to the main wing. The connection assembly has a first actuator unit for moving the flap between the retracted position and at least one extended position. The flap has a leading edge part and a trailing edge part pivotably mounted to the leading edge. The flap has a second actuator unit for moving the trailing edge part relative to the leading edge part within an operating range between an upper operating position and a lower operating position.

Abstract: An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.

Abstract: An aerodynamic system for an aircraft. The aerodynamic system includes a first aerodynamic component configured to be movably coupled to a primary structure of the aircraft, a second aerodynamic component which is movably coupled to the first aerodynamic component and a first panel element coupled to the first aerodynamic component. The first panel element at least partially covers a gap between the first aerodynamic component and the second aerodynamic component. The aerodynamic system further includes a sealing element arranged between the first aerodynamic component and the second aerodynamic component. The sealing element is configured to at least partially block an airflow between the first aerodynamic component and the second aerodynamic component.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connecting assembly movably connecting the slat to the main wing, the slat being movable between retracted and extended positions. The connecting assembly includes a slat track and a roller bearing. A front section of the slat track is mounted to the slat. A rear section and an intermediate section of the slat track are mounted to the main wing via the roller bearing. The roller bearing includes a guide rail mounted to the main wing and a first roller which is rotatably mounted to the rear section of the slat track. The first roller engages a first engagement surface formed by the guide rail. The roller bearing includes a second roller which is rotatably mounted to the main wing. The second roller engages a second engagement surface formed by the intermediate section of the slat track.

Abstract: An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.

Abstract: An arrangement comprising an airfoil body, a junction mechanism for attaching the airfoil body to a support element of an aircraft, and a fairing for aerodynamically covering the junction mechanism. The fairing has a cover element covering a trailing end portion of the fairing. The cover element is attached to the trailing edge of the airfoil body by a form fit connection.

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 wing for an aircraft has a main wing and a trailing edge high lift assembly which has a flap and a connection assembly movably mounting the flap to the main wing. The connection assembly has a first actuator unit for moving the flap between the retracted position and at least one extended position. The flap has a leading edge part and a trailing edge part pivotably mounted to the leading edge. The flap has a second actuator unit for moving the trailing edge part relative to the leading edge part within an operating range between an upper operating position and a lower operating position.