Patent ID: 9248918
Filing Date: 2016-02-02
CPC Classification: B64C,B64D,Y02T

Claim Text:
1. A high lift system for an aircraft comprising a wing box, a flap which is arranged on the wing box and is displaceable with respect to the wing box between a retracted position and at least one extended position by means of a drive device, a support construction which is arranged on the wing box in the region of the drive device to which support construction the flap is coupled and which comprises a movable support element which is movable with respect to the wing box for the displacement of the flap, and an acceleration sensor for the detection of movements of the flap in the form of accelerations of the flap, which sensor is arranged in the region of the flap or the movable support element, wherein an output signal of the acceleration sensor or a quantity derived therefrom is compared with one of a set value and a set curve using an evaluation unit, wherein, using the deviations of the output signal or a quantity derived therefrom from the one of the set value and set curve, unwanted movements caused by a fault in the drive device are detected, and wherein the acceleration sensor is designed as a three-axis acceleration sensor configured to be calibrated to a preset acceleration direction with respect to the acceleration sensor's orientation.