Powered clutch for aircraft wheel drive system

Patent metadata

Field	Value
Publication number	US-10974820-B2
Application number	US-201816133501-A
Country	US
Kind code	B2
Filing date	Sep 17, 2018
Priority date	Jul 26, 2015
Publication date	Apr 13, 2021
Grant date	Apr 13, 2021

Abstract

A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.

First claim

The invention claimed is:

1. A rotary electric power transfer system acutatable to transfer power in an aircraft landing gear wheel drive system, comprising:
a. an aircraft landing gear wheel drive assembly mounted completely within an interior volume defined within wheel wall structures to extend coaxially from an inboard wheel wall structure adjacent a landing gear strut to an outboard wheel wall structure adjacent to an exterior face of a landing gear wheel, said wheel drive assembly comprising at least a drive motor, a drive motor activating system, and an electrically actuatable powered clutch assembly with a pair of clutch plates located within said interior volume in torque transfer engagement and disengagement with said drive motor;
b. a rotary transformer connected to a source of electric power on said aircraft and mounted within said interior volume comprising a stationary element attached to a non-rotating wheel wall structure and a rotary element rotatable with said landing gear wheel, and a power transfer assembly electrically connecting said rotary element with clutch actuator motors located on said exterior face of said landing gear wheel; and
c. a ring gear on said landing gear wheel exterior face driven by said clutch actuator motors, and powered actuator elements driven by said ring gear to engage and lock or to disengage and release said pair of clutch plates when said clutch actuator motors are powered by said rotary transformer.

2. The system of claim 1 , further comprising said drive motor and said drive motor activating system enclosed within a housing in said interior volume secured to a stationary wall structure of said landing gear wheel and in torque transfer contact with said powered clutch assembly, wherein said powered clutch assembly is mounted within said interior volume between a wheel wall structure adjacent to a landing gear wheel axle and said housing.

3. The system of claim 2 , wherein said drive motor comprises an electric drive motor and said drive motor activation system comprises a gear system or a roller traction drive system in torque transfer contact with said electric drive motor.

4. The system of claim 2 , wherein said powered clutch assembly pair of clutch plates comprises at least a pocket plate mounted to rotate with the vehicle landing gear wheel and a notch plate attached to the drive motor activating system, and a retaining ring holds said pocket plate and said notch plate in desired relative positions, and wherein a surface of said pocket plate is configured to engage a spline on said housing.

5. The system of claim 1 , wherein said powered actuator elements comprise axially movable actuation pins with a uniformly cylindrical body section integrally formed with a hammer-shaped actuating head section to engage and lock correspondingly configured receptacles in each one of said pair of clutch plates in response to power transfer from said clutch actuation motors through said ring gear.

6. The system of claim 5 , wherein said ring gear is positioned exteriorly of said exterior face concentric with and radially outwardly of a hub of said landing gear wheel a distance that accommodates said powered actuator elements, and wherein said ring gear is in power transfer contact with said cylindrical body section of said powered actuation elements.

7. The system of claim 1 , wherein said clutch actuator motors comprise at least two clutch actuator motors sized to fit outboard of said landing gear wheel in powering contact with said ring gear.

8. The system of claim 1 , wherein said power transfer assembly comprises wires located in trenches and channels in said wheel wall structures to extend from said rotary transformer to electrically connect with said clutch actuator motors.

9. The system of claim 1 , wherein said rotary transformer stationary element is attached to a non-rotating inboard wheel wall structure adjacent to a torque takeout element located exteriorly of said inboard wheel wall structure.

10. The system of claim 1 , further comprising automatic or manual control means for controlling and directing a supply of electric power from said source of electric power on said aircraft to said rotary transformer.

11. A rotary electric power transfer system acutatable to transfer power in a vehicle wheel drive system, comprising:
a. a vehicle wheel drive assembly mounted completely within an interior volume defined within wheel wall structures to extend coaxially from an inboard wheel wall structure to an outboard wheel wall structure adjacent to an exterior face of a vehicle wheel, said wheel drive assembly comprising at least an electric drive motor, a drive motor activating system, and an electrically actuatable powered clutch assembly with a pair of clutch plates in torque transfer engagement and disengagement with said electric drive motor located within said interior volume;
b. a rotary transformer connected to a source of electric power on said vehicle and mounted within said interior volume comprising a stationary element attached to an inboard non-rotating wheel wall structure, a rotary element rotatable with said vehicle wheel, and a power transfer assembly electrically connecting said rotary element with clutch actuator motors located on said exterior face of said vehicle wheel;
c. a ring gear on said vehicle wheel exterior face driven by said clutch actuator motors and powered actuator elements in contact with and driven by said ring gear to engage and lock or to disengage and release said pair of clutch plates when said clutch actuator motors are powered by said rotary transformer; and
d. automatic or manual control means for controlling and directing a supply of electric power from said source of electric power on said vehicle to said rotary transformer.

Assignees

• Borealis Tech Ltd

Inventors

• Cox Isaiah W
• Cox Joseph J
• Edelson Jonathan S
• Rotenberg Yonatan
• Hanson John

Classifications

• F16D11/14

  with clutching members movable only axially (F16D11/02, F16D11/08 take precedence) · CPC title

• B64C25/00

  Alighting gear (air-cushion alighting gear B60V3/08) · CPC title

• F16D41/06

  with intermediate wedging coupling members between an inner and an outer surface (F16D41/02, F16D41/24 take precedence) · CPC title

• B60K7/0007

  the motor being electric · CPC title

• Y02T50/80

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