Systems and methods for aircraft braking and taxiing

Patent metadata

Field	Value
Publication number	US-9815551-B2
Application number	US-201514803658-A
Country	US
Kind code	B2
Filing date	Jul 20, 2015
Priority date	Jul 20, 2015
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, a system may comprise an electric motor and a clutch. The electric motor may include a first output shaft and a second output shaft. The clutch may selectively engaging the motor to at least one of a driver transmission and a brake transmission, wherein, in response to engagement with the driver transmission, the electric motor drives, exclusively, an aircraft wheel via the first output shaft, wherein, in response to engagement with the brake transmission, the electric motor drives, exclusively, a brake clamping system via the second output shaft to apply force to an aircraft brake disk stack.

First claim

The invention claimed is:

1. A braking and taxiing system comprising:
an electric motor, wherein said electric motor comprises a first output shaft and a second output shaft,
a clutch for selectively engaging the electric motor to at least one of a driver transmission and a brake transmission,
wherein, in response to engagement with the driver transmission, the electric motor drives, exclusively, an aircraft wheel via the first output shaft,
wherein, in response to engagement with the brake transmission, the electric motor drives, exclusively, a brake clamping system via the second output shaft to apply force to an aircraft brake disk stack,
wherein the driver transmission is located on the opposite side of the electric motor as the brake transmission, wherein the electric motor, the driver transmission, and the brake transmission are in concentric alignment.

2. The system of claim 1 , wherein the brake clamping system comprises the brake transmission, a ballscrew and a ram.

3. The system of claim 1 , wherein the first output shaft and the second output shaft are in concentric alignment.

4. The system of claim 1 , wherein the clutch includes a neutral position, wherein, in response to engagement in the neutral position, the electric motor may spin freely.

5. The system of claim 1 , wherein the driver transmission drives rotation of the aircraft wheel.

6. The system of claim 1 , wherein at least one of the driver transmission and the brake transmission comprise a high gear ratio transmission with a gear ratio from about 30:1 to about 110:1.

7. The system of claim 1 , wherein at least one of the driver transmission and the brake transmission includes a planetary gear set.

8. The system of claim 1 , wherein a controller provides a command to the electric motor.

9. The system of claim 8 , wherein an input device provides input to the controller.

10. A system comprising:
an aircraft wheel comprising a mating portion for mating with a driver transmission, the aircraft wheel coupled to an aircraft brake;
the aircraft brake comprising a brake clamping system for selectively engaging a brake disk stack; and
a clutch for selectively engaging an electric motor to at least one of the driver transmission and a brake transmission, the electric motor comprising a centerline axis,
wherein the driver transmission is located on the opposite side, axially, of the electric motor as the brake transmission.

11. The system of claim 10 , wherein in response to engagement with the brake transmission, the electric motor drives the brake clamping system, wherein the brake clamping system comprises the brake transmission, a ballscrew and a ram.

12. The system of claim 10 , wherein in response to engagement with the driver transmission, the electric motor drives the aircraft wheel.

13. The system of claim 10 , wherein the clutch includes a neutral position, wherein, in response to engagement in the neutral position, the electric motor may spin freely.

14. The system of claim 10 , wherein the mating portion is located along an interior circumference of the aircraft wheel.

15. The system of claim 10 , wherein the mating portion comprises a geared portion.

16. The system of claim 10 , wherein the mating portion is integral to the aircraft wheel.

17. The system of claim 10 , wherein the mating portion is detachably coupled to the aircraft wheel.

18. A method comprising:
sending a driver signal to a braking and taxiing system, the braking and taxiing system comprising a clutch and a motor in concentric alignment with a driver transmission and in concentric alignment with a brake transmission; and
selectively engaging, by the clutch, at least one of a first position, a second position, and a third position in response to the driver signal,
wherein, in response to engagement with the first position, a second output shaft of the electric motor is coupled to the brake transmission via the clutch,
wherein, in response to engagement with the second position, a first output shaft of the electric motor is engaged with the driver transmission via the clutch,
wherein, in response to engagement with the third position, the first output shaft and the second output shaft may spin freely.

19. The method of claim 18 , wherein in response to engagement with the first position, the motor drives a brake clamping system, wherein the brake clamping system comprises the brake transmission, a ballscrew, and a ram, wherein in response to engagement with the second position, the motor drives an aircraft wheel.

Assignees

• Goodrich Corp

Inventors

• Drennen David
• Rehfus Kevin

Classifications

• B64C25/36 Primary

  Arrangements or adaptations of wheels, tyres or axles in general · CPC title

• B60T8/1703

  for aircrafts · CPC title

• B64C25/405

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

• B64C25/44

  Actuating mechanisms · CPC title

• Y02T50/80

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