Actuators and methods for aircraft flight control surfaces

Patent metadata

Field	Value
Publication number	US-10689097-B2
Application number	US-201515311200-A
Country	US
Kind code	B2
Filing date	May 13, 2015
Priority date	May 16, 2014
Publication date	Jun 23, 2020
Grant date	Jun 23, 2020

Abstract

Actuators and methods useful in the operation aircraft flight control surfaces are disclosed. Some of the actuators and methods disclosed may be useful in the operation flight control surfaces when a fault condition such as a jam associated with an actuator is detected. An exemplary electromechanical actuator disclosed comprises: a motor; a first screw configured for translation movement relative to a structure of the aircraft when driven by the motor; a second screw mounted in series with the first screw; and a fuse element coupling the first screw and the second screw together to permit translation movement of the second screw together with the first screw. The fuse element may permit at least partial disengagement of the second screw from the first screw to permit translation of the second screw relative to the first screw. The fuse element may also allow an active flutter damping of the flight control surface. The fuse element may comprise magneto-rheological fluid.

First claim

What is claimed is:

1. An electromechanical actuator for actuating a flight control surface of an aircraft, the actuator comprising:
a motor;
a first screw configured for translation movement relative to a structure of the aircraft when driven by the motor;
a second screw mounted in series with the first screw, the first screw and the second screw defining a load path between the aircraft structure and the flight control surface;
a fuse element coupling the first screw and the second screw together to permit translation movement of the second screw together with the first screw, the fuse element permitting at least partial disengagement of the second screw from the first screw to permit translation of the second screw relative to the first screw.

2. The actuator as defined in claim 1 , wherein the second screw is at least partially received inside the first screw.

3. The actuator as defined in claim 1 , wherein the first screw and the second screw are configured to permit telescopic movement of the second screw relative to the first screw when the fuse element at least partially disengages the second screw from the first screw.

4. The actuator as defined in claim 1 , wherein the fuse element comprises magneto-rheological fluid.

5. The actuator as defined in claim 4 , wherein the fuse element comprises a permanent magnet for directing a first magnetic flux through the magneto-rheological fluid.

6. The actuator as defined in claim 5 , wherein the fuse element comprises a coil for receiving a current therethrough for producing a second magnetic flux that redirects at least part of the first magnetic flux away from the magneto-rheological fluid.

7. The actuator as defined in claim 1 , wherein the fuse element functions as a power-off brake.

8. The actuator as defined in claim 1 , wherein the first screw is coupled to the motor via a first nut.

9. The actuator as defined in claim 8 , wherein the first nut is rotatably supported by the aircraft structure.

10. The actuator as defined in claim 1 , wherein the second screw is coupled to the first screw via a second nut.

11. The actuator as defined in claim 10 , wherein the second nut is rotatably supported by the first screw.

12. The actuator as defined in claim 1 , wherein the first screw is coupled to the motor via a gear.

13. The actuator as defined in claim 1 , wherein the first screw is mounted to substantially prevent rotation of the first screw relative to the aircraft structure.

14. The actuator as defined in claim 1 , wherein the second screw is mounted to substantially prevent rotation of the second screw relative to the first screw.

15. An aircraft comprising the actuator as defined in claim 1 .

16. An assembly for actuating a flight control surface of an aircraft, the assembly comprising:
an actuation member configured to be in a load path between the flight control surface and a structure of the aircraft for actuating the flight control surface relative to the aircraft structure; and
a fuse element configured to be in the load path with the actuation member, the fuse element comprising magneto-rheological fluid and a permanent magnet for directing a first magnetic flux through the magneto-rheological fluid.

17. The assembly as defined in claim 16 , wherein the actuation member comprises a screw.

18. The assembly as defined in claim 16 , wherein the actuation member comprises a gear mechanism.

19. The assembly as defined in claim 16 , comprising an electric motor for driving the actuation member.

20. The assembly as defined in claim 16 , wherein the fuse element comprises a coil for receiving a current therethrough for producing a second magnetic flux that redirects at least part of the first magnetic flux away from the magneto-rheological fluid.

21. The assembly as defined in claim 16 , wherein the fuse element functions as a power-off brake.

Assignees

• Bombardier Inc
• Univ Sherbrooke

Inventors

• Nfonguem Gustave
• Chouinard Patrick
• Plante Jean-Sébastien
• Denninger Marc
• Iliescu Vlad

Classifications

• F16H25/205

  comprising alternate power paths, e.g. for fail safe back-up · CPC title

• F16H2025/2071

  Disconnecting drive source from the actuator, e.g. using clutches for release of drive connection during manual control · CPC title

• F16H25/20 Primary

  Screw mechanisms (with automatic reversal F16H25/12) · CPC title

• F16H25/2454

  Brakes; Rotational locks · CPC title

• F16H2025/2081

  Parallel arrangement of drive motor to screw axis · CPC title