Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

Abstract: A foldable wing for an aircraft includes a base wing having a base wing end region, a wing tip having a connection region, a first engagement means integrated into the base wing, a second engagement means integrated into the wing tip, and a drive mechanism coupled with the wing tip for moving the wing tip relative to the base wing. The first and second engagement means are adapted for engaging each other along a sliding course from a first position, in which the connection region of the wing tip and the base wing end region are in a flush contact to form a continuous wing, up to a second position, in which the first engagement means and the second engagement means disengage. The drive mechanism includes a first movement element and a second movement element at least partially extending in a spanwise direction, and supported in a linear guide each.

Abstract: A wing arrangement for an aircraft, comprising a wing having a base section and a tip section pivotably connected to base section such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position. The wing arrangement also comprises a latching arrangement which includes an engagement portion, a latching actuator selectively movable between a first actuator position and a second actuator position, an elastically deformable structure, and a latching element. When the tip section is pivoted from the stowed or deployed position into an engagement position, the elastically deformable structure is initially deformed, and as the tip section pivots further into the deployed or stowed position, the elastic deformation of the elastically deformable structure decreases.

Abstract: A foldable wing for an aircraft includes a base wing having a base wing end region, a wing tip having a connection region, a first engagement means integrated into the base wing, a second engagement means integrated into the wing tip, and a drive mechanism coupled with the wing tip for moving the wing tip relative to the base wing. The first and second engagement means are adapted for engaging each other along a sliding course from a first position, in which the connection region of the wing tip and the base wing end region are in a flush contact to form a continuous wing, up to a second position, in which the first engagement means and the second engagement means disengage. The drive mechanism includes a first movement element and a second movement element at least partially extending in a spanwise direction, and supported in a linear guide each.

Abstract: The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. At least one damping unit for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which can occur as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap.

Abstract: An adjustment system of an aeroplane, having: at least one adjustable flap on each of the wing of an aeroplane, adjustable with an adjustment device, a drive device for purposes of driving the adjustment devices, and a load sensor for purposes of recording the load occurring in the load path between the actuator and the adjustable flap of the respective adjustment device. The load sensor is embodied as a sensor for purposes of measuring the longitudinal force occurring in a drive rod along its longitudinal direction.

Abstract: The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. At least one damping unit for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which can occur as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap.

Abstract: A nut lock or locking cap secures a nut on a bolt so that the nut cannot loosen itself and so that the nut cannot fall off the bolt. For this purpose the nut lock has a first ring section that at least partially surrounds the bolt and a second ring section that at least partially surrounds the nut. The two ring sections are interconnected by a radially extending flange, whereby the first ring section has a smaller diameter than the diameter of the second ring section. The first ring section has at least one through-hole that can be aligned with a cross-bore in the bolt for the insertion of a locking pin. The second ring section has radially inwardly facing profiled surfaces that enter into a form-locking, force-transmitting connection with the outer profile of the nut.

Abstract: An actuation device for a slat, a rail for guiding and moving the slat into and out of an aircraft wing has the slat pivoted on the rail in a particular point (8); a thrust rod has one end hinged to the slat and a drive crank is connected to a second end of the thrust rod; a lever assembly connects the rail additionally to the slat at points on the rail and the slat different from the particular point and for pivoting and steering the slat relative to the particular point, for holding the rear end of the slat against the wing in a first protraction range and opening a gap upon further protraction.