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The present invention relates to a high lift system for an aircraft, comprising a flap, which is arranged on a wing box and which can be moved between a retracted position and at least one extended position relative to the wing box by means of a drive device, a support construction, which is arrange

The present invention relates to a high lift system for an aircraft, comprising a flap, which is arranged on a wing box and which can be moved between a retracted position and at least one extended position relative to the wing box by means of a drive device, a support construction, which is arranged on the wing box in the area of the drive device and to which the flap is coupled and which comprises a movable support element, which can be moved to move the flap relative to the wing box, and an acceleration sensor arranged in the area of the flap or the movable support element for detecting accelerations of the flap.

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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

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, andan 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. 2. The high lift system according to claim 1, wherein the movable support element is rotatably mounted relative to the wing box with respect to a flap axis of rotation and the flap attached to the movable support element rotates relative to the wing box with respect to the flap axis of rotation upon rotation of the movable support element. 3. The high lift system according to claim 1, wherein the acceleration sensor is arranged on the movable support element or on the flap. 4. The high lift system according to claim 1, wherein the acceleration sensor is arranged on an end of the movable support element which faces the flap. 5. The high lift system according to claim 1, wherein the flap is a landing flap. 6. The high lift system according to claim 1, comprising a further drive device, by means of which the flap is displaceable between a retracted position and at least one extended position with respect to the wing box,a further support construction which is arranged on the wing box in the region of the further drive device, to which support construction the flap or is coupled and which comprises a further movable support element which is movable with respect to the wing box for the displacement of the flap, anda further acceleration sensor for the detection of accelerations of the flap, which sensor is arranged in the region of the flap or the further movable support element. 7. An aerofoil for an aircraft comprising a high lift system according to claim 1. 8. The aerofoil according to claim 7, wherein the aerofoil comprises a plurality of high lift systems having a plurality of flaps having drive devices and support constructions, and that acceleration sensors for the detection of accelerations of the flaps are arranged on a plurality or all of the flaps or movable support elements of the support constructions. 9. An aircraft comprising at least one aerofoil according to claim 7 and comprising an evaluation unit connected to the acceleration sensor for the evaluation of sensor signals of the acceleration sensor. 10. A method for detection of faults in a high lift system for an aircraft comprising a flap which is arranged on a 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, and a support construction which is arranged on the wing box, 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, wherein movement of the flap in the form of acceleration of the flap is detected using a three-axis acceleration sensor,the acceleration sensor is calibrated with respect to the acceleration sensor's spatial orientation when the aircraft is in an idle state,an output signal of the acceleration sensor or a quantity derived therefrom is compared with a set value or a set curve using an evaluation unit and,using the deviations of the output signal or a quantity derived therefrom from the set value or set curve, unwanted movement caused by a fault in the drive device is detected. 11. The method according to claim 10, wherein the aircraft comprises at least one further drive device, by means of which the flap or a further flap is displaceable between a retracted position and at least one extended position with respect to a wing box of the aircraft,at least one further support construction which is arranged on the wing box in the region of the further drive device, to which support construction the flap or the further flap is coupled and which comprises a further movable support element which is movable with respect to the wing box for the displacement of the flap or the further flap, andat least one further acceleration sensor for the detection of accelerations of the flap or the further flap, which sensor is arranged in the region of the flap or the further flap or the further movable support element, the signals of the acceleration sensors being evaluated by the evaluation unit in such a way that output signals which are detected by all acceleration sensors in equal or almost equal measure are not considered for the fault detection. 12. The method according to claim 10, wherein the three-axis acceleration sensor is calibrated with respect to the acceleration sensor's spatial orientation relative to the gravitational pull vector. 13. 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, andan 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 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. 14. The high lift system according to claim 13, wherein the three-axis acceleration sensor is calibrateable with respect to the acceleration sensor's spatial orientation relative to the gravitational pull vector. 15. The high lift system according to claim 1, wherein the three-axis acceleration sensor is calibrateable with respect to the acceleration sensor's spatial orientation relative to the gravitational pull vector. 16. 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;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 a set value or a set curve using an evaluation unit, 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; at least one further drive device, by means of which the flap or a further flap is displaceable between a retracted position and at least one extended position with respect to a wing box of the aircraft;at least one further support construction which is arranged on the wing box in the region of the further drive device, to which support construction the flap or the further flap is coupled and which comprises a further movable support element which is movable with respect to the wing box for the displacement of the flap or the further flap; andat least one further acceleration sensor for the detection of accelerations of the flap or the further flap, which sensor is arranged in the region of the flap or the further flap or the further movable support element, wherein an output signal of the further acceleration sensor or a quantity derived therefrom is compared with a set value or a set curve using an evaluation unit, wherein the further acceleration sensor is designed as a three-axis acceleration sensor configured to be calibrated to a preset acceleration direction with respect to the further acceleration sensor's orientation, the evaluation unit being configured to evaluate the signals of the acceleration sensors in such a way that using the deviations of the output signal or a quantity derived therefrom from the set value or set curve, unwanted movements caused by a fault in the drive device are detected, wherein output signals which are detected by all acceleration sensors in equal or almost equal measure are not considered by the evaluation unit for the fault detection.