Patent ID: 8061652

Claim:
A rudder of a commercial aircraft, comprising: a division along a longitudinal direction of the rudder in at least one region; a plurality of flap parts of the rudder spread against an air flow surrounding the commercial aircraft by means of an actuator for decelerating the commercial aircraft; a joint base that is supported articulatedly on the commercial aircraft and is turnable by means of the actuator for lateral control of the commercial aircraft; a first flap part of the rudder supported in an articulated fashion relative to the joint base and spreadable against the air flow surrounding the commercial aircraft by means of the actuator in order to decelerate the commercial aircraft; and a second flap part of the rudder rigidly connected to the joint base, wherein the first flap part of the rudder supported in an articulated fashion is turned relative to the joint base by means of the actuator for spreading the rudder and the second part of the rudder that is rigidly connected to the joint base is pivoted toward an opposite side together with the joint base by means of the actuator for the lateral control of the commercial aircraft in order to realize a symmetric excursion of the first part and second part during the spreading of the rudder, wherein further the first part includes a first brake flap, the second part includes a secon brake flap, and the first brake flap and the second brake flap are substantially symmetrical.