Patent ID: 8302913

Claim:
A high-lift system for an aircraft, comprising: a wing; a high-lift flap coupled to the wing; a kinematic element which is driven by a drive device; a flap lever structured and arranged to rotate via an actuating drive between a retracted position, in which the high-lift flap complements a wing profile, and a plurality of extended positions, in which a slot of a given width is formed between the wing and the high-lift flap; a first end of the flap lever being coupled to the high-lift flap; a second end of the flap lever being coupled to the kinematic element and being capable of rotating relative thereto via a first rotation point; the kinematic element being structured and arranged to rotate relative to a second rotation point that is fixed in position relative to the wing, wherein the first rotation point is separated by a predetermined distance from the second rotation point; wherein the high-lift flap is structured and arranged to assume the following positions upon rotation of the kinematic element: a retracted or cruise flight position, whereby the high-lift flap continuously complements the wing profile and the first rotation point assumes a first position with respect to an aircraft longitudinal direction and an aircraft vertical direction; a first extended or take-off position, whereby the first rotation point assumes a second position located under the first position with respect to the aircraft vertical direction and forward of the first position with respect to the aircraft longitudinal direction; and a second extended or landing position, whereby the first rotation point assumes a third position which is located aft of the second position with respect to the aircraft longitudinal direction and above the second position with respect to the aircraft vertical direction.