Landing gear drive system

Patent metadata

Field	Value
Publication number	US-11524771-B2
Application number	US-201916409592-A
Country	US
Kind code	B2
Filing date	May 10, 2019
Priority date	Aug 7, 2014
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.

First claim

The invention claimed is:

1. A drive system for rotating a wheel of an aircraft landing gear, the drive system including
a motor operable to rotate a drive pinion, and
a driven gear adapted to be mounted to the wheel,
wherein the drive system has
a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and
a second configuration in which the drive pinion is not capable of meshing with the driven gear, and

the drive system further comprises a linear positioning actuator for moving the drive pinion relative to the driven gear, wherein the positioning actuator has a first end and a second end,
the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and
the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion and
further comprising a locking device external to the positioning actuator for locking the drive system in the second configuration.

2. A drive system according to claim 1 , wherein the positioning actuator is back-driveable.

3. A drive system according to claim 1 , wherein one of the drive pinion and the driven gear comprises a sprocket and the other of the drive pinion and the driven gear comprises a series of rollers arranged to form a ring, each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the drive pinion or driven gear, respectively.

4. A drive system according to claim 1 , wherein the wheel is driveable for taxiing the aircraft on the ground and/or spinning-up the wheel prior to landing.

5. A drive system according to claim 1 , wherein the motor is a motor/generator which, when operating as a generator, is configured to apply a braking torque to the wheel.

6. An aircraft landing gear having a drive system according to claim 1 .

7. A drive system according to claim 1 , wherein the positioning actuator includes an hydraulic cylinder.

8. A drive system according to claim 7 , wherein the hydraulic cylinder is dual acting.

9. A drive system according to claim 7 , wherein the hydraulic cylinder is single acting.

10. A drive system according to claim 9 , wherein the hydraulic cylinder has an annular section on one side of a piston and a cylindrical section on the other side of the piston, and the cylindrical section is un-pressurised.

11. A drive system according to claim 10 , wherein the un-pressurised section is vented via a liquid tight gas permeable membrane.

12. A drive system according to claim 9 , wherein the hydraulic cylinder has a first rod and a second rod forming two annular sections between the first and second rods, the two annular sections are fluidly coupled to a single hydraulic port.

13. A drive system according to claim 12 , wherein the two annular sections have dissimilar areas.

14. A drive system according to claim 1 , wherein the positioning actuator is a self-locking actuator.

15. A drive system according to claim 14 , wherein the self-locking actuator is arranged to lock the drive system in the second configuration.

16. A drive system according to claim 1 , further comprising an unlocking actuator arranged to release the locking device.

17. A drive system according to claim 16 , wherein the unlocking actuator is configured to release the locking device when the positioning actuator is commanded to move the drive pinion from the second configuration to the first configuration.

18. A drive system according to claim 16 , wherein the locking device includes a mechanical locking lever.

19. A drive system according to claim 16 , wherein the unlocking actuator includes an hydraulic cylinder.

20. A drive system according to claim 19 , wherein the positioning actuator includes an hydraulic cylinder, wherein the hydraulic unlocking actuator and the hydraulic positioning actuator are coupled to a common hydraulic supply.

21. A drive system according to claim 1 , wherein the locking device includes a mechanical locking lever.

22. A drive system according to claim 21 , wherein the locking device includes a hook pivotally mounted on the aircraft landing gear and a pin spaced at a fixed distance from the axis of rotation of the drive pinion, wherein the hook is moveable between a locked position in which the pin is held captive by the hook, and an unlocked position in which the pin moves relative to the hook.

23. A drive system according to claim 22 , further comprising a latch moveable between a locked and an unlocked position, where the latch in the locked position engages the hook and prevents pivotal movement of the hook, and the latch in the unlocked position permits pivotal movement of the hook.

24. A drive system according to claim 23 , further comprising an unlocking actuator arranged to release the locking device, wherein the unlocking actuator is coupled to the latch for disengaging the latch from the hook.

25. A drive system according to claim 1 , further comprising a biasing element for biasing the drive system to the second configuration.

26. A drive system according to claim 25 , wherein the biasing element includes at least one spring.

27. A drive system according to claim 26 , wherein the spring is a leaf spring.

28. A drive system according to claim 26 , wherein the spring is a compression spring.

29. A drive system according to claim 28 , wherein the compression spring is restrained by a guide to avoid buckling of the spring.

30. A drive system according to claim 1 , wherein the driven gear is adapted to be mounted to a hub of the wheel.

31. A drive system according to claim 30 , wherein the driven gear is adapted to be mounted to an outer rim of the hub.

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

33. A drive system according to claim 32 , when the bracket includes two lugs comprising half-moon clamps to permit ready attachment and detachment of the bracket.

34. A drive system for rotating a wheel of an aircraft landing gear, the drive system including
a motor operable to rotate a drive pinion,
a driven gear adapted to be mounted to the wheel,
wherein the drive system has
a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear such that the drive system is engaged, and
a second configuration in which the drive pinion is not capable of meshing with the driven gear such that the drive system is disengaged,

wherein the drive system further comprises a linear positioning actuator for moving the drive pinion relative to the driven gear,
wherein the positioning actuator has a first end and a second end,
the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and
the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion, and

wherein the drive system further comprises a locking device external to the positioning actuator for locking the drive system in the second

Assignees

• Airbus Operations Ltd

Inventors

• Didey Arnaud

Classifications

• F16H1/06

  with parallel axes · CPC title

• B64C25/34 Primary

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C25/405 Primary

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

• Y02T50/80

  Energy efficient operational measures, e.g. ground operations or mission management · CPC title

• B64C25/40

  the elements being rotated before touch-down · CPC title