Abstract: The invention relates to a device for load limitation in a aircraft high lift system, said system comprising individual segments of landing flap systems and slat flap systems, and a drive unit. The inventive device for load limitation comprises a control unit that is connected to position sensors and is embodied in such a way as to process signals from the position sensors and to generate a signal for limiting the supplied drive power. The invention also relates to a method for load limitation. According to said method, signals from at least two position sensors are measured; at least one reference variable is calculated form the measured signals; each reference variable is compared with a corresponding threshold value pre-determined from a maximum authorized load; and a control signal is generated for limiting the drive power, when at least one of the reference variables reaches or exceeds the threshold value.

Abstract: A drive and guidance apparatus for a trailing-edge/landing flap,-arranged on an aircraft mainplane, the apparatus comprising a six-element guide chain having seven rotating joints and one or more shafts; a first coupling element mounted via a crank connected to the mainplane wherein the crank can rotate, the coupling is connected to the flap and to a second coupling element wherein the first coupling can rotate, the second coupling mounted on the mainplane wherein the second coupling can rotate. The second coupling element is connected to the flap via an oscillating support. The crank is arranged wherein the rotation direction of the crank for extension of the flap corresponds to the rotation direction of the crank for the trailing-edge flap of the starboard wing of the mainplane, with the rotation direction of the crank for the trailing-edge flap of the starboard wing being counterclockwise when viewed from the aircraft fuselage.

Abstract: A drive and guidance apparatus for a flap which is arranged on an aircraft mainplane, in particular for a trailing-edge or landing flap, comprising a six-element guide chain with seven rotating joints with one or more shafts. In this case, a first coupling element, which is mounted via a crank that is connected to the aircraft mainplane such that it can rotate, itself in turn is connected to the flap and to a second coupling element such that it can rotate, which is mounted on the aircraft mainplane such that it can rotate. In this case, the second coupling element is connected to the flap via an oscillating support. According to the invention, the crank is arranged in such a manner that the rotation direction of the crank for extension of the flap corresponds to the rotation direction of the crank for the trailing-edge flap of the starboard wing, with the rotation direction of the crank for the trailing-edge flap of the starboard wing being counterclockwise when viewed from the aircraft fuselage.

Abstract: The invention relates to a device for load limitation in a aircraft high lift system, said system comprising individual segments of landing flap systems and slat flap systems, and a drive unit. The inventive device for load limitation comprises a control unit that is connected to position sensors and is embodied in such a way as to process signals from the position sensors and to generate a signal for limiting the supplied drive power. The invention also relates to a method for load limitation. According to said method, signals from at least two position sensors are measured; at least one reference variable is calculated form the measured signals; each reference variable is compared with a corresponding threshold value pre-determined from a maximum authorized load; and a control signal is generated for limiting the drive power, when at least one of the reference variables reaches or exceeds the threshold value.