Abstract: An aircraft having two separate landing flaps on each wing which are actuated together in a landing mode or function, and wherein the outer flap of each wing is also separately actuated in an aileron mode or function separate from the inner flap.

Abstract: In an aircraft having two separate landing flaps on a wing and which are together actuated in a landing mode or function, the outer flap is also separately actuated in an aileron mode or function apart from the inner flap.

Abstract: The present invention relates to an aircraft having at least one flap arranged at the wing of the aircraft and having at least one first drive unit for actuating the flap as a landing flap and a first control unit for controlling the first drive unit when the aircraft is in a landing mode of operation, wherein the aircraft comprises at least one second drive unit which is an active differential gear box for actuating the flap as an aileron and a second control unit for controlling the second drive unit when the aircraft performs an aileron function.

Abstract: The invention relates to an aircraft having at least one high lift system which is arranged at the wing of the aircraft and which comprises a drive for converting electrical or hydraulic energy into a speed-controlled rotational movement, wherein the aircraft furthermore has at least one control unit which controls the high lift system, wherein the drive comprises in accordance with the invention a main drive and an alternative drive, wherein the alternative drive is fed by a decentralized energy source.

Abstract: The invention relates to an aircraft having at least one high lift system which is arranged at the wing of the aircraft and which comprises a drive for converting electrical or hydraulic energy into a speed-controlled rotational movement, wherein the aircraft furthermore has at least one control unit which controls the high lift system, wherein the drive comprises in accordance with the invention a main drive and an alternative drive, wherein the alternative drive is fed by a decentralized energy source.

Abstract: The present disclosure relates to an aircraft high lift system with at least one load station for actuating a flap of a wing, preferably a landing flap and/or a leading-edge flap, at least one transmission with transmission portions located between branch transmissions, wherein by means of the branch transmissions actuating energy can be branched off from the transmission to the load station, and to a method for determining an operating condition of an aircraft high lift system.

Abstract: This invention discloses a method for activating a drive system for control surfaces or working systems of an aircraft, wherein the speed of a drive unit of the drive system is regulated, and after a starting operation the maximum driving power available during the further operation for speed regulation of the drive unit is reduced. Likewise, this invention comprises a drive system for control surfaces or working systems of an aircraft, comprising a drive unit with speed regulation and a corresponding control.

Abstract: An aeronautical high-lift system comprising a drive unit, elements for the transmission of the drive energy to drive stations of individual segments of landing flap/slat flap systems as well as comprising an overload safety device, with the overload safety device having at least one electrical overload sensor which is arranged in the drive chain between the drive unit and an output drive station.

Abstract: The present disclosure relates to an aircraft high lift system with at least one load station for actuating a flap of a wing, preferably a landing flap and/or a leading-edge flap, at least one transmission with transmission portions located between branch transmissions, wherein by means of the branch transmissions actuating energy can be branched off from the transmission to the load station, and to a method for determining an operating condition of an aircraft high lift system.

Abstract: This invention discloses a method for activating a drive system for control surfaces or working systems of an aircraft, wherein the speed of a drive unit of the drive system is regulated, and after a starting operation the maximum driving power available during the further operation for speed regulation of the drive unit is reduced. Likewise, this invention comprises a drive system for control surfaces or working systems of an aircraft, comprising a drive unit with speed regulation and a corresponding control.

Abstract: An aeronautical high-lift system comprising a drive unit, elements for the transmission of the drive energy to drive stations of individual segments of landing flap/slat flap systems as well as comprising an overload safety device, with the overload safety device having at least one electrical overload sensor which is arranged in the drive chain between the drive unit and an output drive station.