Drive system for landing gear and drive system control method

Patent metadata

Field	Value
Publication number	US-10112703-B2
Application number	US-201515123293-A
Country	US
Kind code	B2
Filing date	Mar 5, 2015
Priority date	Mar 5, 2014
Publication date	Oct 30, 2018
Grant date	Oct 30, 2018

Abstract

A method for controlling a separation between rotational axes of a pair of meshing gears is disclosed. A parameter indicative of a transmission error through the gears is measured and the separation is controlled, aiming to minimise variations in the measured signal. This acts to reduce variations in transmission error and the related vibrations created in the drive system and in the surrounding components. A related drive system and aircraft landing gear are described.

First claim

The invention claimed is:

1. A drive system for an aircraft landing gear comprising:
first and second gears for engagement to transfer a drive input to the system between the first and second gears;
an actuator for adjusting a distance between rotational axes of the first and second gears;
a sensor configured to detect at least one parameter indicative of a transmission error through the first and second gears; and
a controller configured to control the actuator to adjust a distance between respective rotational axes of the gears, in response to the detected parameter, when the first and second gears are engaged to minimise the transmission error.

2. A drive system according to claim 1 , wherein the detected parameter comprises a distance measured between respective rotational axes of the first and second gears.

3. A drive system according to claim 1 , wherein the detected parameter comprises a torque measured at one or more points in a drive path from a motor to a wheel of an aircraft landing gear where the drive path includes the first and second gears.

4. A drive system according to claim 3 , wherein the detected parameter comprises a torque differential between two points in the drive path, the two points being one on either side of the engagement between the first and second gears.

5. A drive system according to claim 1 , wherein the detected parameter comprises a current draw of a motor providing drive input to the drive system.

6. A drive system according to claim 1 , wherein the detected parameter comprises a current demand at a motor controller for controlling a motor providing drive input to the drive system.

7. A drive system according to claim 1 , wherein the detected parameter comprises a rotational velocity at one or more points in a drive path from a motor to a wheel of an aircraft landing gear where the drive path includes the first and second gears.

8. A drive system according to claim 7 , wherein the detected parameter comprises a rotational velocity differential between two points in the drive path, the two points being one on either side of the engagement between the first and second gears.

9. A drive system according to claim 1 , wherein the controller is arranged for controlling the actuator to adjust the distance between respective rotational axes of the gears in response to a measurement of an amplitude of an oscillation of the detected parameter, or a rate of change of amplitude of an oscillation of the detected parameter.

10. A drive system according to claim 1 , wherein the controller is arranged for controlling the actuator to adjust the distance between respective rotational axes of the gears to minimise an amplitude of an oscillation of the detected parameter, and the controller is arranged for controlling the actuator based on an amplitude of oscillation of the detected parameter.

11. A drive system according to claim 1 , wherein the controller is arranged for controlling the actuator to adjust the distance between respective rotational axes of the gears to minimise a vibration induced in the drive system.

12. A drive system according to claim 1 , wherein the controller is arranged for monitoring the detected parameter to identify a wear condition of the first and/or second gears.

13. A drive system according to claim 1 , wherein the first gear is a roller gear comprising a series of rollers arranged to form a ring, each roller being rotatable about a roller axis located at a fixed distance from the rotational axis of the first gear; and wherein the second gear is a sprocket comprising an array of sprocket teeth for engagement with the rollers of the first gear.

14. An aircraft landing gear drive system comprising a drive system according to claim 1 , wherein the first and second gears are arranged for connecting a drive input from a motor to a wheel of the landing gear via the first and second gears.

15. An aircraft landing gear drive system according to claim 14 , wherein the drive system has:
a first configuration in which the first gear is capable of meshing with the second gear to connect a drive input from the motor to the wheel, and
a second configuration in which the first gear is not capable of meshing with the second gear.

16. An aircraft landing gear drive system according to claim 15 , wherein an actuator is arranged to move the landing gear drive system between the first and second configurations.

17. An aircraft landing gear drive system according to claim 16 , wherein the same actuator is used to move the landing gear drive system between the first and second configurations and to adjust the distance between rotational axes of the first and second gears in the first configuration.

18. An aircraft landing gear drive system according to claim 14 , wherein one of the first and second gears is attached to the wheel of the landing gear, preferably at an outer diameter of the wheel hub.

19. An aircraft landing gear drive system according to claim 15 , wherein movement of the landing gear drive system in the first configuration is limited by a stop, and the actuator for adjusting the distance between rotational axes of the first and second gears is coupled to the stop for moving the stop.

20. A drive system or aircraft landing gear according to claim 1 , wherein the drive system is supported by a bracket which is rigidly connected to the axle, main fitting or slider part of the landing gear.

21. A drive system or aircraft landing gear according to claim 20 , wherein the bracket includes two lugs comprising half-moon clamps to permit ready attachment and detachment of the bracket.

22. A method of controlling engagement of first and second gears in a drive system, comprising the steps of:
detecting at least one parameter indicative of a transmission error through first and second gears of the drive system; and
automatically adjusting a distance between respective rotational axes of the gears using an actuator in response to the detected parameter to minimise the transmission error.

23. A method according to claim 20 , wherein the drive system comprises first and second gears for engagement to transfer a drive input to the system between the first and second gears; an actuator for adjusting a distance between rotational axes of the first and second gears; a sensor for detecting at least one parameter indicative of a transmission error through the first and second gears; and a controller for controlling the actuator to adjust a distance between respective rotational axes of the gears, in response to the detected parameter, when the first and second gears are engaged to minimise the transmission error, and wherein the first and second gears are arranged for connecting a drive input from a motor to a wheel of the landing gear via the first and second gears.

Assignees

• Airbus Operations Ltd

Inventors

• Wilson Fraser

Classifications

• F16H1/26

  Special means compensating for misalignment of axes · CPC title

• F16H57/12 Primary

  Arrangements for adjusting or for taking-up backlash not provided for elsewhere · CPC title

• F16H57/0006

  Vibration-damping or noise reducing means specially adapted for gearings (devices for varying tension of belts, ropes or chains with damping means F16H7/0829; toothed members with construction providing vibration damping F16H55/14; reducing vibrations or noise of the gearbox casing F16H57/028; suppression of vibrations or noise of gear selectors F16H59/0208; control of hydrostatic fluid gearing preventing or reducing vibrations or noise F16H61/4183) · CPC title

• F16H57/01

  Monitoring wear or stress of gearing elements, e.g. for triggering maintenance · CPC title

• F16H1/06

  with parallel axes · CPC title