High lift system for an aircraft

Patent metadata

Field	Value
Publication number	US-9278751-B2
Application number	US-201314044960-A
Country	US
Kind code	B2
Filing date	Oct 3, 2013
Priority date	Apr 7, 2011
Publication date	Mar 8, 2016
Grant date	Mar 8, 2016

Abstract

A high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor.

First claim

What is claimed is:

1. A high lift system for an aircraft, the high lift system comprising:
a fully electric drive including an electric motor which drives a landing flap of the high lift system,
wherein the electric motor has internal redundancy due to redundant windings,
wherein the internal redundancy is configured as an m×n phase topology,
wherein n phases of the electric motor are combined into a phase group in each case, resulting in m submotors,
wherein the electric motor is configured in such a way that all m submotors are connected, without a gear unit, to a single shaft of the electric motor,
wherein the drive further comprises control electronics of the electric motor, and the control electronics are configured in such a way that if at least one of the submotors and the phase groups fail, they bring about an increase in current within the remaining intact submotors and phase groups, and
wherein the control electronics are configured to carry out the current increase in such a way that it does not cause the torque to fall below a nominal torque.

2. The high lift system according to claim 1 ,
wherein the electric motor comprises only one drive train.

3. The high lift system according to claim 2 ,
wherein the individual submotors are configured in such a way that they each provide at least one of the same rotational speed and the same torque.

4. The high lift system according to claim 1 ,
wherein each submotor provides a torque, and
wherein the electric motor is configured in such a way that the torques of the submotors are added to drive the landing flap.

5. The high lift system according to claim 1 ,
wherein the electric motor is configured in such a way that if at least one of the submotors and the phase groups fail, a predefined motor output power is provided by the rest of the electric motor, which remains intact.

6. The high lift system according to claim 1 ,
wherein the high lift system comprises the landing flap, and a nominal torque is required for the landing flap to be driven by the electric motor, and
wherein the electric motor is configured in such a way that if at least one of the submotors and the phase groups fail, the nominal torque for driving the landing flap is provided by the rest of the electric motor, which remains intact.

7. The high lift system according to claim 1 ,
wherein the electric motor has a 3×3 phase topology, and
wherein the electric motor has single redundancy, and thus each of the 3 submotors provide about 50% of a predefined nominal torque for driving the landing flap.

8. The high lift system according to claim 1 ,
wherein the electric motor has a 2×3 phase topology, and
wherein the electric motor has single redundancy, and thus each of the two submotors provide a total predefined nominal torque for driving the landing flap.

9. The high lift system according to claim 1 ,
wherein the high lift system is configured to drive the landing flap exclusively electrically.

10. The high lift system according to claim 1 ,
wherein the electric motor is configured in such a way that a failure of at least one of the submotors and the phase groups does not affect the rotational speed of the electric motor.

11. The high lift system according to claim 1 ,
wherein the drive has a single internally redundant brake for locking.

12. An aircraft, comprising:
a high lift system that includes a fully electric drive having an electric motor which drives a landing flap of the high lift system,
wherein the electric motor has internal redundancy due to redundant windings, and the internal redundancy is configured as an m×n phase topology,
wherein n phases of the electric motor are combined into a phase group in each case, resulting in m submotors,
wherein the electric motor is configured in such a way that all m submotors are connected, without a gear unit, to a single shaft of the electric motor,
wherein the drive further comprises control electronics of the electric motor, and the control electronics are configured in such a way that if at least one of the submotors and the phase groups fail, they bring about an increase in current within the remaining intact submotors and phase groups, and
wherein the control electronics are configured to carry out the current increase in such a way that it does not cause the torque to fall below a nominal torque.

13. The aircraft according to claim 12 ,
wherein n phases of the electric motor are combined into a phase group in each case, resulting in m submotors, and
wherein the electric motor is configured in such a way that all m submotors are connected, without a gear unit, to a single shaft of the electric motor.

14. The aircraft according to claim 13 ,
wherein the electric motor comprises only one drive train.

15. The aircraft according to claim 14 ,
wherein the individual submotors are configured in such a way that they each provide at least one of the same rotational speed and the same torque.

16. The aircraft according to claim 13 ,
wherein each submotor provides a torque, and
wherein the electric motor is configured in such a way that the torques of the submotors are added to drive the landing flap.

17. The aircraft according to claim 13 ,
wherein the electric motor is configured in such a way that if at least one of the submotors and the phase groups fail, a predefined motor output power is provided by the rest of the electric motor, which remains intact.

18. The aircraft according to claim 13 ,
wherein the high lift system comprises the landing flap, and a nominal torque is required for the landing flap to be driven by the electric motor, and
wherein the electric motor is configured in such a way that if at least one of the submotors and the phase groups fail, the nominal torque for driving the landing flap is provided by the rest of the electric motor, which remains intact.

Assignees

• Airbus Operations Gmbh

Inventors

• Christmann Markus
• Giebeler Christoph
• Recksiek Martin
• Dorr Bjoern

Classifications

• B64C13/24

  Transmitting means · CPC title

• B64C9/22

  at the front of the wing · CPC title

• B64C9/16 Primary

  at the rear of the wing · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• B64C13/50

  using electrical energy · CPC title