Granted Patent B2

US 12,422,001 · App. 18/303,155 · Granted Sep 23, 2025

Inventors: Karl Potier (Paris, FR); Maxime Serrand (Paris, FR)

Assignee: GOODRICH ACTUATION SYSTEMS SAS

F16D7/007B64C13/28

Abstract

Claims (30)

1. An asymmetric torque limiter having an axis of rotation (A) comprising:

a first annular friction disk;

a second annular friction disk concentrically arranged with the first annular friction disk;

a skewed roller disk in contact with the second annular friction disk, wherein the skewed roller disk includes a plurality of skewed rollers mounted in an annular retainer, wherein the plurality of skewed rollers are each rotatable about a respective roller axis, each roller axis being skewed with respect to a radial direction passing through the skewed roller from the axis of rotation (A);

a first resilient member attached to the first annular friction disk and configured to bias the first annular friction disk toward an input shaft; and

a second resilient member configured to bias the skewed roller disk toward the second annular friction disk.

2. The asymmetric torque limiter of claim 1 , comprising an annular spacer mounted between the second resilient member and the skewed roller disk, wherein the annular spacer is in contact with the skewed roller disk.

3. The asymmetric torque limiter of claim 1 , wherein the second annular friction disk is arranged radially outwardly of first annular friction disk.

4. The asymmetric torque limiter of claim 1 , wherein the second annular friction disk is arranged radially inwardly of the first annular friction disk.

5. The asymmetric torque limiter of claim 1 , wherein the first resilient member comprises a Belleville spring.

6. The asymmetric torque limiter of claim 1 , wherein the second resilient member comprises a Belleville spring.

7. The asymmetric torque limiter of claim 1 , wherein each of the first and the second annular friction disks are carbon friction disks.

8. The asymmetric torque limiter of claim 1 , wherein each roller axis is skewed at an angle (α) of 45 degrees with respect to the radial direction passing through the skewed roller from the axis of rotation (A).

9. An assembly, comprising:

an input shaft;

an output shaft coaxial with the input shaft; and

an asymmetric torque limiter as recited in claim 1 mounted axially between the input shaft and the output shaft.

10. The assembly of claim 9 , wherein the output shaft comprises an outer circumferential ring located radially outwardly of the skewed roller disk.

11. The assembly of claim 9 , comprising:

a static body;

a thrust bearing mounted axially between a portion of the static body and a portion of the input shaft.

12. An aircraft wing comprising:

a flight control surface; and

the assembly of claim 9 , wherein the output shaft is configured to actuate the flight control surface.

13. An aircraft comprising the aircraft wing of claim 12 .

14. A method of passively limiting torque asymmetrically using the asymmetric torque limiter of claim 1 , the method comprising:

providing an input shaft with a first input torque in one of a clockwise and anticlockwise direction and transmitting the first input torque from the input shaft to an output shaft when the first input torque is less than a first torque threshold and preventing transmission of torque higher than the first torque threshold when the first input torque is greater than the first torque threshold; and

providing the input shaft with a second input torque in the other of the clockwise and anticlockwise direction and transmitting the second input torque from the input shaft to the output shaft when the second input torque is less than a second torque threshold and preventing transmission of torque higher than the second torque threshold when the second input torque is greater than the second torque threshold,

wherein the second torque threshold is larger than the first torque threshold.

15. The method of claim 14 , wherein providing the input shaft with the second input torque deploys a flight control surface and providing the input shaft with the first input torque retracts the flight control surface.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (21)