Device for determining the rotation angle of a shaft in an aircraft

1. An aircraft having a device for determining the rotation angle of a shaft in the aircraft, the device comprising:

a shaft designed for operating a component, the component selected from the group consisting of a brake flap, a landing flap, a landing slat, a rudder, an aileron and an elevator, the shaft having a first region and a second region,

a motor which rotates the shaft to detect first rotation data corresponding to a first rotation angle of the first region of the shaft, the motor being designed to carry out said detection in an absolute manner;

a position pickup unit designed to detect second rotation data corresponding to a second rotation angle of the second region of the shaft;

a synchronization unit designed to synchronize the first rotation data with the second rotation data; and

a control unit designed to provide a calibration procedure which determines a zero point of the motor on the basis of the second rotation data provided by the position pickup unit.

2. The aircraft of claim 1 ,

wherein the motor is designed to transmit the first rotation data to the control unit;

wherein the control unit is designed to control or regulate the rotation of the shaft on the basis of the transmitted first rotation data.

3. The aircraft of claim 1 ,

wherein the motor is designed to transmit the first rotation data to the control unit;

wherein the position pickup unit is designed to transmit the second rotation data to the control unit;

wherein the control unit is designed to control or regulate the rotation of the shaft on the basis of the transmitted first and second rotation data.

4. The aircraft of claim 3 ,

wherein the control unit is designed control or regulate the rotation of the shaft only on the basis of the transmitted first rotation data when the transmitted second rotation data is faulty or incomplete.

5. The aircraft of claim 3 ,

wherein the control unit is designed to control or regulate the rotation of the shaft on the basis of the transmitted first and second rotation data, even if the transmitted second rotation data is faulty or incomplete.

6. An aircraft having a device for determining the rotation angle of a shaft in the aircraft, the device comprising:

a shaft designed for operating a component the component selected from the group consisting of a brake flap, a landing flap, a landing slat, a rudder, an aileron and an elevator, the shaft having a first region and a second region,

a motor which rotates the shaft to detect first rotation data corresponding to a first rotation angle of the first region of the shaft, the motor being designed to carry out said detection in an absolute manner;

a position pickup unit designed to detect second rotation data corresponding to a second rotation angle of the second region of the shaft;

a synchronization unit designed to synchronize the first rotation data with the second rotation data; and

a control unit designed to detect and evaluate an incorrectness of the second rotation data provided by the position pickup unit on the basis of the first rotation data.

7. The aircraft of claim 6 ,

wherein the motor is designed to transmit the first rotation data to the control unit;

wherein the control unit is designed to control or regulate the rotation of the shaft on the basis of the transmitted first rotation data.

8. The aircraft of claim 6 ,

wherein the motor is designed to transmit the first rotation data to the control unit;

wherein the position pickup unit is designed to transmit the second rotation data to the control unit;

wherein the control unit is designed to control or regulate the rotation of the shaft on the basis of the transmitted first and second rotation data.

9. The aircraft of claim 8 ,

wherein the control unit is designed control or regulate the rotation of the shaft only on the basis of the transmitted first rotation data when the transmitted second rotation data is faulty or incomplete.

10. The aircraft of claim 8 ,

wherein the control unit is designed to control or regulate the rotation of the shaft on the basis of the transmitted first and second rotation data, even if the transmitted second rotation data is faulty or incomplete.

11. A method for determining the rotation angle of a shaft in an aircraft, comprising the steps of:

rotating the shaft by a motor;

detecting first rotation data that corresponds to a first rotation angle of a first region of the shaft by the motor in an absolute manner;

detecting second rotation data that corresponds to a second rotation angle of a second region of the shaft by a position pickup unit;

transmitting the first rotation data from the motor to a control unit;

transmitting the second rotation data from the position pickup unit to the control unit;

determining a zero point of the motor on the basis of the second rotation data provided by the position pickup unit;

synchronizing the first rotation data with the second rotation data; and

controlling or regulating the rotation of the shaft on the basis of the transmitted first and second rotation data by the control unit.

12. A method for determining the rotation angle of a shaft in a aircraft, comprising the steps of:

rotating the shaft by a motor;

detecting first rotation data that corresponds to a first rotation angle of a first region of the shaft by the motor in an absolute manner;

detecting second rotation data that corresponds to a second rotation angle of a second region of the shaft by a position pickup unit;

transmitting the first rotation data from the motor to a control unit;

transmitting the second rotation data from the position pickup unit to the control unit;

detecting and evaluating an incorrectness of the second rotation data provided by the position pickup unit on the basis of the first rotation data;

synchronizing the first rotation data with the second rotation data; and

controlling or regulating the rotation of the shaft on the basis of the transmitted first and second rotation data by the control unit.