Methods and apparatus to measure multiple control surfaces with a sensor

Patent metadata

Field	Value
Publication number	US-11926437-B2
Application number	US-201916457096-A
Country	US
Kind code	B2
Filing date	Jun 28, 2019
Priority date	Jun 28, 2019
Publication date	Mar 12, 2024
Grant date	Mar 12, 2024

Abstract

Methods and apparatus to measure multiple control surfaces with a sensor are disclosed. A disclosed example apparatus for determining a condition associated with first and second control surfaces includes a sensor to measure a rotation of a shaft operatively coupled thereto. The apparatus also includes a first differential operatively coupled between the shaft and a first pivot of the first control surface, and a second differential operatively coupled between the first differential and a second pivot of the second control surface.

First claim

What is claimed is:

1. An apparatus for determining a condition associated with first and second control surfaces, the apparatus comprising,
a sensor to measure a rotation of a shaft operatively coupled thereto;
a first differential operatively coupled between the shaft and a first pivot of the first control surface, the shaft operatively coupled to an input of the first differential and the first pivot operatively coupled to an output of the first differential; and
a second differential operatively coupled between the first differential and a second pivot of the second control surface, the output of the first differential operatively coupled to an input of the second differential and the second pivot operatively coupled to an output of the second differential.

2. The apparatus as defined in claim 1 , further including a third differential operatively coupled between the second differential and a third pivot of a third control surface.

3. The apparatus as defined in claim 1 , further including a processor communicatively coupled to the sensor to determine the condition based on the measured rotation of the shaft.

4. The apparatus as defined in claim 3 , wherein the processor is to determine the condition based on comparing the measured rotation to at least one expected rotational value.

5. The apparatus as defined in claim 1 , further including a spring operatively coupled to the shaft.

6. The apparatus as defined in claim 5 , wherein the spring is to rotate the shaft to a baseline rotation when a driveline disconnect failure associated with at least one of the first or second differentials occurs.

7. The apparatus as defined in claim 1 , wherein the first and second control surfaces are flaps for an aircraft.

8. The apparatus as defined in claim 1 , wherein the first and second differentials are arranged across a span of an aerodynamic body.

9. The apparatus as defined in claim 8 , wherein the first and second differentials are sequentially arranged along the span of the aerodynamic body.

10. The apparatus as defined in claim 1 , wherein the rotation of the shaft is the summed rotation of the first and second differentials, and wherein the summed rotation indicates an operational condition of the first and second control surfaces.

11. The apparatus as defined in claim 1 , wherein a first axis of rotation of the first pivot is aligned with a second axis of rotation of the second pivot.

12. An aerodynamic body for use with a vehicle, the aerodynamic body comprising:
first and second control surfaces;
at least one actuator to move the first and second control surfaces;
a shaft;
first and second differentials, the first differential operatively coupled between the shaft and a first pivot associated with the first control surface, the second differential operatively coupled between the first differential and a second pivot associated with the second control surface, the shaft operatively coupled to an input of the first differential and the first pivot operatively coupled to an output of the first differential, the output of the first differential operatively coupled to an input of the second differential and the second pivot operatively coupled to an output of the second differential; and
a rotational sensor operatively coupled to the shaft, wherein the rotational sensor is to measure a rotation of the shaft to determine a condition associated with the first and second control surfaces.

13. The aerodynamic body as defined in claim 12 , further including a processor to determine the condition based on comparing the measured rotation to at least one expected rotational value.

14. The aerodynamic body as defined in claim 13 , wherein the at least one expected rotational value includes a first rotational value corresponding to an expected value for a retracted position of the first and second control surfaces, and a second rotational value corresponding to an expected value for an extended position of the first and second control surfaces.

15. The aerodynamic body as defined in claim 12 , wherein the aerodynamic body is a wing, and wherein the first and second control surfaces are flaps.

16. The aerodynamic body as defined in claim 15 , wherein the flaps are Krueger flaps.

17. The aerodynamic body as defined in claim 15 , further including a flap controller to vary a movement of the first and second control surfaces based on the determined condition.

18. The aerodynamic body as defined in claim 12 , further including a spring operatively coupled to the shaft to rotate the shaft to a baseline rotation in response to a driveline disconnect failure associated with the first and second control surfaces.

19. A non-transitory machine readable medium comprising instructions, which when executed, cause a processor to at least:
determine a rotational displacement of a shaft operatively coupled to a first differential, wherein the first differential is operatively coupled between the shaft and a first pivot associated with a first control surface, and wherein a second differential is operatively coupled between the first differential and a second pivot associated with a second control surface, the shaft operatively coupled to an input of the first differential and the first pivot operatively copuled to an output of the first differential, the output of the first differential operatively coupled to an input of the second differential and the second pivot operatively coupled to an output of the second differential;
compare the determined rotational displacement to at least one expected rotational value; and
calculate a condition of at least one of the first or second control surfaces based on the comparison.

20. The non-transitory machine readable medium as defined in claim 19 , wherein the instructions cause the processor to direct movement of at least one of the first or second control surfaces based on the calculated condition.

21. The non-transitory machine readable medium as defined in claim 19 , wherein the at least one expected rotational value includes a first rotational value corresponding to a retracted position of the first and second control surfaces, and a second rotational value corresponding to an extended position of the first and second control surfaces.

22. The non-transitory machine readable medium as defined in claim 19 , wherein the condition is calculated to determine whether one of the first or second control surfaces has deviated from an intended rotational displacement.

23. The non-transitory machine readable medium as defined in claim 19 , wherein the condition is calculated by determining a presence of a driveline disconnect failure.

24. The non-transitory machine readable medium as defined in claim 19 , wherein the instructions cause the processor to calculate first and second rotational displacements of the first and second control surfaces, respectively, based on the rotational displacement of the shaft.

25. The non-transitory machine readable medium as defined in claim 19 , wherein the instructions cause the processor to determine first and second rotational orientations of the first and second control surfaces, respectively, based on the measured orientation.

26. The non-transitory machine readable medium as defined in claim 19 , wherein the instructions cause the processor to determine whether at least one of the first or second control surfaces is overextended or underextended based

Assignees

• Boeing Co

Inventors

• Good Mark S

Classifications

• B64F5/60 Primary

  Testing or inspecting aircraft components or systems · CPC title

• B64C9/26

  by multiple flaps · CPC title

• B64C13/00 Primary

  Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers · CPC title

• B64D45/0005 Primary

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title

• B64D2045/001

  for indicating symmetry of flaps deflection · CPC title