Drive system for rotating a wheel of a landing gear having a transmission error measurement apparatus

Patent metadata

Field	Value
Publication number	US-11514728-B2
Application number	US-201916285668-A
Country	US
Kind code	B2
Filing date	Feb 26, 2019
Priority date	Feb 27, 2018
Publication date	Nov 29, 2022
Grant date	Nov 29, 2022

Abstract

A drive system 20, 20′ for rotating a wheel 11, 11′ of an aircraft landing gear 10, 10 ′, is disclosed having a drive element 24, 24 ′, a motor 21, 21′ operable to rotate the drive element, and a driven gear 25, 25′ adapted to be attached to the wheel. The drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, wherein the drive system further comprises a transmission error measurement apparatus 30, 40 , the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear. An aircraft 100 and a method of providing an indication of a transmission error in a drive system is disclosed.

First claim

The invention claimed is:

1. A drive system for rotating a wheel of an aircraft landing gear, the drive system comprising:
a drive element,
a motor operable to rotate the drive element, and
a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel,

wherein the drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear,
wherein the drive system further comprises a transmission error measurement apparatus, the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear, and
wherein the apparatus is configured to compare a characteristic of the measurement data of a cycle to the same characteristic of the measurement data of a previous cycle, whereby the difference of the compared characteristics is an indication of the transmission error.

2. A drive system as claimed in claim 1 , wherein the transmission error measurement apparatus comprises a data transfer device so that the measurement data obtained can be transferred for later analysis.

3. A drive system as claimed in claim 1 , wherein the transmission error measurement apparatus comprises a data storage device so that the measurement data obtained can be stored for later analysis.

4. An aircraft comprising the drive system of claim 1 .

5. A drive system as claimed in claim 1 , wherein the drive element and driven gear comprise a roller gear and sprocket.

6. A drive system as claimed in claim 5 , wherein the drive element comprises a roller gear and the driven gear comprises a sprocket.

7. A drive system as claimed in claim 1 , wherein the transmission error measurement apparatus comprises a speed sensor device, for measuring, over time, a rotational speed of a part of the drive system when in the drive configuration.

8. A drive system as claimed in claim 7 , wherein the speed sensor device is located on the drive element or driven gear for measuring, over time, a rotational speed of the drive element or driven gear, respectively, when in the drive configuration.

9. A drive system as claimed in claim 8 , wherein the speed sensor device is located on the drive element for measuring, over time, a rotational speed of the drive element when in the drive configuration.

10. A drive system as claimed in claim 7 , wherein the transmission error measurement apparatus comprises a motor speed indication measurement device, for measuring, over time, an indication of the rotational speed of the motor when in the drive configuration.

11. A drive system as claimed in claim 10 , wherein the motor speed indication measurement device comprises i) a motor speed sensor device for measuring, over time, a rotational speed of the motor when in the drive configuration, or ii) a motor current measurement device for measuring, over time, a supplied current to the motor when in the drive configuration.

12. A drive system as claimed in claim 10 , wherein the motor speed indication measurement device is also configured to be used, upon approach to landing of the aircraft, to match the rotational speed of the motor to a flight speed of the aircraft, prior to the drive system being configured in the drive configuration.

13. A drive system as claimed in claim 1 , wherein the transmission error measurement apparatus comprises a torque sensor device, for measuring, over time, a torque on a part of the drive system when in the drive configuration.

14. A drive system as claimed in claim 13 , wherein the torque sensor device is located on the drive element or driven gear for measuring, over time, a rotational torque on the drive element or driven gear, respectively, when in the drive configuration.

15. A drive system as claimed in claim 14 , wherein the torque sensor device is located on the drive element for measuring, over time, a rotational torque on the drive element when in the drive configuration.

16. A drive system as claimed in claim 13 , wherein the transmission error measurement apparatus comprises a motor torque indication measurement device, for measuring, over time, an indication of the rotational torque provided by the motor when in the drive configuration.

17. A drive system as claimed in claim 16 , wherein the motor torque indication measurement device comprises i) a motor torque sensor device for measuring, over time, a rotational torque provided by the motor when in the drive configuration, or ii) a motor current measurement device for measuring, over time, a supplied current to the motor when in the drive configuration.

18. A drive system for rotating a wheel of an aircraft landing gear, the drive system comprising:
a drive element,
a motor operable to rotate the drive element, and
a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel,

wherein the drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear,
wherein the drive system further comprises a transmission error measurement apparatus comprising a vibration sensor device, for measuring, over time, vibrations on a part of the drive system, the transmission error measurement apparatus being configured to use vibration data resulting from the vibration sensor device to provide and indication of a transmission error.

19. A drive system as claimed in claim 18 , wherein the vibration sensor device comprises an accelerometer.

20. A drive system as claimed in claim 18 , wherein the vibration sensor device includes a filter to filter out vibrations caused by isolated events.

21. A drive system as claimed in claim 18 , wherein the vibration sensor device is located on a part of the drive system that does not rotate when the driven gear is driven in the drive configuration.

22. A drive system as claimed in claim 21 , wherein the non-rotating part may be a casing of the motor or gearbox.

23. A method of providing an indication of a transmission error in a drive system for rotating a wheel of an aircraft landing gear, the drive system comprising a drive element, a motor operable to rotate the drive element, and a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel, wherein the method includes the steps of:
configuring the drive system in a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, and
obtaining, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear, and
wherein the method comprises comparing a characteristic of the measurement data of a cycle to the same characteristic of the measurement data of a previous cycle, whereby the difference of the compared characteristics is an indication of the transmission error.

24. A method as claimed in claim 23 , wherein the measurement data obtained is transferred, either by streaming or by a data connection, to a computer and wherein the computer analyses the data or wherein the measurement data is at least partly analysed by t

Assignees

• Airbus Operations Ltd

Inventors

• Crane Nicholas
• Didey Arnaud

Classifications

• B64C25/405 Primary

  Powered wheels, e.g. for taxing · CPC title

• F16H55/10

  Constructively simple tooth shapes, e.g. shaped as pins, as balls · CPC title

• B64C25/40 Primary

  the elements being rotated before touch-down · CPC title

• G07C5/006 Primary

  Indicating maintenance · CPC title

• G07C5/0841

  Registering performance data (recording measured values G01D; information storage G11B) · CPC title