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 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 flight control surface assembly for mounting to a main wing of an aircraft includes flight control surfaces side by side with a gap between each two of them, a connection assembly for movably connecting the flight control surfaces to the main wing to be selectively movable in a predetermined synchronous movement between retracted and extended positions, a drive arrangement operable to effect predetermined synchronous movement, and a control unit connected to the drive arrangement to control the drive arrangement. The flight control surface assembly includes for each gap a separate pair of electrical components with a first electrical component and a second electrical component fixedly mounted to a another one of the two flight control surfaces separated by the gap. The first and second electrical components of each pair are configured to wirelessly transfer electrical energy over the gap.

Abstract: A flight control surface assembly for mounting to a main wing of an aircraft includes flight control surfaces side by side with a gap between each two of them, a connection assembly for movably connecting the flight control surfaces to the main wing to be selectively movable in a predetermined synchronous movement between retracted and extended positions, a drive arrangement operable to effect predetermined synchronous movement, and a control unit connected to the drive arrangement to control the drive arrangement. The flight control surface assembly includes for each gap a separate pair of electrical components with a first electrical component and a second electrical component fixedly mounted to a another one of the two flight control surfaces separated by the gap. The first and second electrical components of each pair are configured to wirelessly transfer electrical energy over the gap.

Abstract: An aircraft having a high lift system, including a control computer, high lift bodies on each wing, a drive coupled to these, an activation device connected to the drive via an analog connection, an input device, and sensors detecting a state of the high lift bodies connected via analog lines to the activation device. The input device connects via a digital connection to the activation device for transmitting commands for adjusting the high lift bodies. The activation device is installed in the payload area of the fuselage and in an area extending from a location spaced from the front of the wingbox by a distance of one third of the fuselage length extending from there to the aircraft's tip, as far as a location spaced from the rear of the wingbox by a distance of one third of the fuselage length extending from there to the aircraft's tail end.

Abstract: An aircraft having a high lift system, including a control computer, high lift bodies on each wing, a drive coupled to these, an activation device connected to the drive via an analog connection, an input device, and sensors detecting a state of the high lift bodies connected via analog lines to the activation device. The input device connects via a digital connection to the activation device for transmitting commands for adjusting the high lift bodies. The activation device is installed in the payload area of the fuselage and in an area extending from a location spaced from the front of the wingbox by a distance of one third of the fuselage length extending from there to the aircraft's tip, as far as a location spaced from the rear of the wingbox by a distance of one third of the fuselage length extending from there to the aircraft's tail end.