Patent ID: 9108724
Filing Date: 2015-08-18
Classification: B64C,B64D,Y02T

Abstract:
1. An adjustment system for a fault-tolerant aeroplane adjustable flap system, the adjustment system comprising: at least one adjustable flap, supported by an articulation device and adjustable on each wing of an aeroplane; at least one adjustment device for adjustment of the adjustable flap, wherein each of the adjustment device comprises: an actuator and a kinematic adjustment mechanism for kinematic coupling of the actuator to the adjustable flap with a drive rod, wherein the drive rod is coupled via a first articulation to the actuator and via a second articulation to the adjustable flap; at least one drive device for driving the adjustment device; a load sensor for capturing a load occurring in a load path between the actuator and the adjustable flap of the respective adjustment device, the load sensor measuring longitudinal force occurring in the drive rod along a longitudinal direction; and a control and monitoring device functionally connected with the at least one drive device for adjustment of the adjustment device and functionally connected with the load sensor for receiving sensor signals generated by the load sensor; wherein the drive rod is formed from a first drive rod section articulated on the actuator, a second drive rod section articulated on the adjustable flap, and a transverse pin coupling these, wherein the drive rod sections are arranged partially overlapping one another with a formation of an overlap region, and the transverse pin for producing a force-transferring coupling of the drive rod sections passes through the drive rod sections in their overlap region transverse to the longitudinal direction of the drive rod; and the load sensor is a sensor arranged on the transverse pin for determining transverse forces acting on the transverse pin, which result from forces occurring in the drive rod.