Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: A flap system driving a leading-edge flap between retracted and extended positions comprises a leading-edge flap having first and second flap joints, first and second scissor links, a first connecting link, and an actuator. The actuator couples with either the first scissor link or first connecting link. The first scissor link is rotatable supported on a first fixed point by a first support joint. An end of the first scissor link opposite the first support joint couples with the first flap joint. The first connecting link is rotatably supported on a second fixed point by a second support joint. An end of the first connecting link opposite the second support joint rotatably couples with an end of the second scissor link. An opposite end of the second scissor link couples with the second flap joint. The first and second scissor links are rotatably coupled to form a scissor arrangement.

Abstract: A high-lift device connection assembly (24) for movably connecting a high lift device (16) to a wing (14) of an aircraft (10) wherein a track (30) is movably guided between main rollers (38, 40, 42, 44). In order to provide an enhanced fall back safety feature in case of a failure of a roller the invention proposes a track catcher (92) to be attached to a structure (26) of the wing (14) and configured to bear a load imposed by the track (30) in case of a main roller failure, wherein the track catcher (92) has at least one first hook element (94, 94-1-94-4) engaged within a first recession (72) at a first side of the track (30) and at least one second hook element (96, 96-1-96-4) engaged with a second recession (74) at the second side of the track (30). Further, the invention relates to a wing and an aircraft equipped with such high-lift device connection assembly (24).

Abstract: A wing for an aircraft includes a main wing, slat, and connection assembly movably connecting the slat to the main wing, wherein the slat is movable between a retracted position and an extended position. The connection assembly includes a guide rail and an elongate slat track extending along a track longitudinal axis between front and rear ends, the front end of the slat track fixedly mounted to the slat. A first roller unit is mounted to the rear end of the slat track engaging the guide rail. A roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface of the slat track. The slat track includes a slot extending through the slat track along the track longitudinal axis. The second roller unit includes a first roller element and a second roller element mounted on one common shaft for common rotation, and the common shaft proceeds through the slot.

Abstract: A wing (5) for an aircraft (1) including a main wing (11) and a high lift assembly (13) having a high lift body (15), and a connection assembly (17) movably connecting the high lift body (15) to the main wing (11), wherein the connection assembly (17) includes a first connection element (19) and a second connection element (21) movably mounted to the main wing (11) and mounted to the high lift body (15), wherein the connection assembly (17) includes a first drive unit (27) drivingly coupled to the first connection element (19), a second drive unit (29) drivingly coupled to the second connection element (21) and a third connection element (57) movably mounted to the main wing (11) and mounted to the high lift body (15), the third connection element (57) is arranged between the first connection element (19) and the second connection element (21).

Abstract: An aircraft structure (11) for flow control including a perforated panel (13) having an inner surface (15) directed to a structure interior (17), an outer surface (19) in contact with an ambient flow (21), and a plurality of micro pores (23) connecting the inner and outer surfaces (15, 19). Elongate crack stopper elements (25) are attached to the inner surface (15) of the perforated panel (13). The crack stopper elements (25) are configured to inhibit crack propagation within the perforated panel (13).

Abstract: A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

Abstract: A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.

Abstract: A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to the high lift body. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to the high lift body. The first output section includes a first drive arm drivingly coupled to the high lift body via at least one first link element rotatably coupled to the first drive arm and mounted to the high lift body.

Abstract: A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to a first connection element. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to a second connection element. The first output section includes a first output wheel and the second output section includes a second output wheel.

Abstract: A wing for an aircraft is disclosed including a main wing, a leading edge high lift assembly having a leading edge high lift body, and a connection assembly movably connecting the leading edge high lift body to the main wing, wherein the connection assembly includes a drive system that is mounted to the main wing and connected to the leading edge high lift body for driving the leading edge high lift body between the retracted position and the extended position. The drive system includes a first drive unit and a second drive unit, the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section coupled to a first connection element and including a first output wheel. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section coupled to a second connection element and including a second output wheel.

Abstract: A heated leading edge structure for an aircraft, including a leading edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, and including a heater device mounted to the inner surface of the leading edge panel for heating of the leading edge panel. The heater device is mounted to the inner surface of the leading edge panel in a detachable manner to provide a simple, lightweight and cost-efficient leading edge structure that enables a simple, quick and efficient maintenance.

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: In order to improve linear drives on aircraft with regards to backlash, gear reduction, self-lock capability, load transfer and wear, a linear drive device is provided that has a first member with engaging teeth, such as a tooth rack and a second member which functions as a drive unit. The second member includes a plurality of movable teeth that are actuated by a cam shaft. The cam shaft has a control cam portion that is shaped such that the movable teeth perform a wave-like motion that forces the first member along its longitudinal direction relative to the second member.

Abstract: In order to provide a track drive device for an aircraft that has zero backlash, a large gear reduction, the ability to self-lock, and a better load transfer and reduced wear, the track drive device drives a track member through a drive device that has at least one drive unit that is arranged adjacent to the track member. Each drive unit comprises a plurality of engaging members that are driven by a cam shaft or a cam gear such that the engaging members are sequentially shifted in a wave-like pattern which results in the track member being moved in a linear manner relative to the drive device along a longitudinal direction.

Abstract: A wing for an aircraft is disclosed including a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail.

Abstract: A wing for an aircraft is disclosed having a main wing, a slat, and a connection assembly movable connecting the slat to the main wing, wherein the connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing comprising a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail, and wherein the roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.

Abstract: A leading edge assembly for an aircraft wing. The leading edge assembly includes a housing configured to be connectable to a fixed wing section of the wing, the housing formed with a first opening connecting an exterior of the housing with an interior of the housing, an actuating element movably connected to the housing, such that the actuating element is movable between a first position and at least one second position. The actuating element extends through the first opening and includes a first section arranged in the interior of the housing and a second section arranged at the exterior of the housing. The actuating element is configured to be connectable to a high lift device.

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 actuator arrangement for a fixed leading edge member of an aircraft wing. The fixed leading edge member has an inner cavity defined by the outer skin and ribs. The actuator arrangement comprises at least one geared rotary actuator which moves relative to the other parts along a circular arc section during extending and retracting of the high-lift device between a fully retracted position and a fully extended position. In the fully retracted position, the actuator is predominantly accommodated within the inner cavity and in the extended position the actuator is predominantly positioned outside the inner cavity, preferably protruding through a D-nose cut-out.