Patent ID: 8444094
Filing Date: 2013-05-21
Classification: B64C

Abstract:
1. A high-lift system for an aircraft, comprising: a main wing, a lift flap, a flap adjustment mechanism operating to couple the lift flap to the main wing of the aircraft, such that the lift flap is adjustable, between a retracted position and several extended positions relative to the main wing of the aircraft, and a drive device operating to actuate the flap adjustment mechanism, wherein: the flap adjustment mechanism comprises at least two adjustment devices arranged so as to be spaced apart from each other in a wingspan direction of the main wing, each adjustment device comprises a first lever and a second lever, each of the first and second levers including a respective length between opposing end pieces thereof, where a first end piece of each of the two levers includes a rotational coupling to the main wing, and a second end piece of each of the two levers includes a rotational coupling to the lift flap, at least one of the at least two adjustment devices being arranged such that at least one of the rotational couplings is a displaceable rotational coupling which is free to rotate and free to displace along a path with respect to the main wing or the lift flap, and the flap adjustment mechanism further comprises a displacement guiding mechanism positioned between the displaceable rotational coupling and the rotational coupling at the opposing end piece, and including: (i) a pivot element in fixed position with respect to the main wing or the lift flap to which the displaceable rotational coupling is connected, and (ii) a guide extending in a longitudinal direction on one of the first and second levers, wherein one of the first and second levers is a displaceable lever, wherein, the pivot element is slidably engaged with the longitudinal guide such that the displaceable lever rotates about the pivot element and displaces as the pivot element slides with respect to the longitudinal guide.