Drive system for aircraft landing gear

Patent metadata

Field	Value
Publication number	US-11066154-B2
Application number	US-201916297109-A
Country	US
Kind code	B2
Filing date	Mar 8, 2019
Priority date	Apr 1, 2014
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates. An engagement command is issued to an actuator at an engagement time, and the actuator operates the actuator in response to the engagement command to move the pinion from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time operating the actuator to move the pinion further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position.

First claim

The invention claimed is:

1. A method of engaging a drive system with a rotating wheel of an aircraft landing gear, the method comprising:
operating a motor to apply torque to a pinion so the pinion rotates; issuing an engagement command to an actuator at an engagement time;
operating the actuator in response to the engagement command to move the pinion from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to the rotating wheel of the aircraft landing gear;
then after the initial contact time operating the actuator to move the pinion further to a meshing position where the pinion meshes with the driven gear, wherein a centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position, and the method further comprises
operating the motor to reduce the torque to below a predetermined level at or after the engagement time, maintain the torque below the predetermined level until the initial contact time, then after the initial contact time increase the torque above the predetermined level, and
wherein the driven gear contacts the pinion in a series of impacts as the pinion moves from the contact position to the meshing position, each impact induces a spike in electromotive force or angular velocity at the motor, and the method further comprising operating the motor to increase the torque above the predetermined level after the initial contact time in response to the detection of one of the spikes.

2. The method of claim 1 wherein the method comprises operating the motor to reduce the torque to substantially zero at or after the engagement time, maintain the torque at substantially zero until the initial contact time, then after the initial contact time increase the torque above substantially zero.

3. The method of claim 1 wherein the pinion or driven gear is a roller gear with rollers which mesh with teeth of the driven gear or pinion, respectively.

4. The method of claim 1 wherein the method comprises increasing the torque above the predetermined level after the pinion has moved to the meshing position.

5. The method of claim 1 wherein the method comprises increasing the torque above the predetermined level before the pinion has moved to the meshing position.

6. The method of claim 1 wherein the driven gear has N gear teeth or rollers, the pinion has N pinion teeth or rollers which mesh with the teeth or rollers of the driven gear when the pinion is at the meshing position, the pinion and driven gear are rotating at angular velocities ω pinion and ω gear respectively at the initial contact time, and a sync ratio ((ω pinion *N pinion )/(ω gear *N gear )) at the initial contact time is not 1.

7. The method of claim 6 wherein the sync ratio ((ω pinion *N pinion )/(ω gear *N gear )) at the initial contact time is less than 0.98 or greater than 1.02.

8. The method of claim 6 wherein the sync ratio ((ω pinion *N pinion )/(ω gear *N gear )) at the initial contact time is less than 1.

9. The method of claim 8 wherein the sync ratio ((ω pinion *N pinion )/(ω gear *N gear )) at the initial contact time is less than 0.98.

10. The method of claim 9 wherein the sync ratio ((ω pinion *N pinion )/(ω gear *N gear )) at the initial contact time is less than 0.96.

11. A drive system for rotating a wheel of an aircraft landing gear, the drive system comprising:
a pinion;
a driven gear adapted to be mounted to the wheel of the aircraft landing gear;
a motor arranged to apply torque to the pinion so the pinion rotates;
an actuator which is responsive to an engagement command at an engagement time to move the pinion from a neutral position to a contact position in which it contacts the driven gear at an initial contact time;
then after the initial contact time to move the pinion further to a meshing position where the pinion meshes with the driven gear, wherein a centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position, and the drive system further comprises a controller which is configured to operate the motor to reduce the torque to below a predetermined level at or after the engagement time, maintain the torque below the predetermined level until the initial contact time, then after the initial contact time increase the torque above the predetermined level, and
wherein the driven gear is configured to contact the pinion in a series of impacts as the pinion mover from the contact position to the meshing position, each impact induces a spike in electromotive force or angular velocity at the motor, and wherein the motor is configured to increase the torque above the predetermined level after the initial contact time in response to the detection of one of the spikes.

12. The drive system according to claim 11 , wherein the drive system is supported by a bracket which is rigidly connected to an axle, main fitting or slider part of the landing gear.

13. The drive system according to claim 12 , wherein the bracket includes two lugs comprising half-moon clamps to permit ready attachment and detachment of the bracket.

Assignees

• Airbus Operations Ltd

Inventors

• Morris James

Classifications

• Y02T50/80

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

• B64C25/40 Primary

  the elements being rotated before touch-down · CPC title

• B64C25/405 Primary

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

• F16H1/06

  with parallel axes · CPC title

• B64C25/42

  Arrangement or adaptation of brakes · CPC title