Aircraft electric brake actuator assembly with line replaceable actuator brake

Patent metadata

Field	Value
Publication number	US-9815438-B2
Application number	US-70497110-A
Country	US
Kind code	B2
Filing date	Feb 12, 2010
Priority date	Feb 12, 2010
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

An aircraft electric brake actuator assembly includes an actuator housing, a motor housing, an actuator, an electric motor, and an actuator brake. The actuator housing is configured to be mounted on an aircraft landing gear. The motor housing is coupled to the actuator housing and is removable therefrom. The motor housing is also accessible when the actuator housing is mounted on an aircraft. The electric motor is disposed within the motor housing and is coupled to the actuator. The actuator brake is disposed within the motor housing and is removably coupled to the motor.

First claim

What is claimed is:

1. An aircraft electric brake actuator assembly, comprising:
an actuator housing configured to be mounted on an aircraft landing gear;
a motor housing coupled to the actuator housing and removable therefrom, the motor housing being accessible when the actuator housing is mounted on the aircraft landing gear;
an actuator disposed within the actuator housing, the actuator being coupled to receive a drive torque and configured, upon receipt of the drive torque, to translate to a position;
an electric motor disposed within the motor housing and coupled to the actuator, the electric motor being configured to be selectively energized and configured, upon being energized, to rotate and thereby supply the drive torque to the actuator;
an actuator brake disposed within the motor housing and removably coupled to the motor, the actuator brake being configured to selectively engage and disengage the motor to thereby at least inhibit motor rotation and allow motor rotation, respectively, wherein the motor housing envelopes at least a portion of the electric motor and the actuator brake; and
a mounting bolt, wherein the actuator brake is removably coupled to the motor via the mounting bolt.

2. The actuator assembly of claim 1 , wherein:
the electric motor includes a rotationally mounted shaft; and
the actuator brake at least selectively engages the shaft.

3. The actuator assembly of claim 2 , wherein the actuator brake is electrically operated.

4. The actuator assembly of claim 3 , further comprising:
an electric connector extending from the motor; and
a plurality of electrically conductive pins extending from the actuator brake and removably connected to the electric connector.

5. The actuator assembly of claim 4 , wherein:
the motor includes a first end and a second end;
the shaft extends from the first end; and
the electric connector extends from the second end.

6. The actuator assembly of claim 4 , further comprising a plurality of actuator brake power conductors extending through the motor to the electric connector, the actuator brake power conductors being configured to couple to a direct current (DC) electric power source.

7. The actuator assembly of claim 3 , wherein the actuator brake is configured to (i) engage the motor when it is electrically de-energized and (ii) disengage the motor when it is electrically energized.

8. An aircraft electric brake actuator assembly, comprising:
an actuator housing configured to be mounted on an aircraft landing gear;
a motor housing coupled to the actuator housing and removable therefrom, the motor housing being accessible when the actuator housing is mounted on the aircraft landing gear;
an actuator disposed within the actuator housing, the actuator coupled to receive a drive torque and configured, upon receipt of the drive torque, to translate to a position;
an electric motor disposed within the motor housing and coupled to the actuator, the electric motor being configured to be selectively energized and configured, upon being energized, to rotate and thereby supply the drive torque to the actuator, wherein the motor includes a first end and a second end, and a rotationally mounted shaft extending from the first end;
an electrically operated actuator brake disposed within the motor housing and removably coupled to the motor, the actuator brake being configured to selectively engage and disengage the motor to thereby at least inhibit motor rotation and allow motor rotation, respectively, wherein the motor housing envelopes at least a portion of the electric motor and the actuator brake, wherein the actuator brake at least selectively engages the rotationally mounted shaft of the electric motor;
an electric connector extending from the second end of the motor; and
a plurality of electrically conductive pins extending from the actuator brake and removably connected to the electric connector.

9. The actuator assembly of claim 8 , further comprising a plurality of actuator brake power conductors extending through the motor to the electric connector, the actuator brake power conductors being configured to couple to a direct current (DC) electric power source.

10. The actuator assembly of claim 8 , wherein the actuator brake is configured to (i) engage the motor when it is electrically de-energized and (ii) disengage the motor when it is electrically energized.

11. An aircraft electric brake actuator assembly, comprising:
an actuator housing configured to be mounted on an aircraft;
a motor housing coupled to the actuator housing and removable therefrom, the motor housing being accessible when the actuator housing is mounted on an aircraft landing gear;
an actuator disposed within the actuator housing, the actuator coupled to receive a drive torque and configured, upon receipt of the drive torque, to translate to a position;
an electric motor disposed within the motor housing and coupled to the actuator, the electric motor including a first end, a second end, and a rotationally mounted shaft extending from the first end, the motor being configured to be selectively energized and configured, upon being energized, to rotate and thereby supply the drive torque to the actuator;
an electrically operated actuator brake disposed within the motor housing and removably coupled to the motor, the actuator brake being configured to be selectively de-energized and energized to selectively engage and disengage the shaft, respectively, and thereby at least inhibit motor rotation and allow motor rotation, respectively, wherein the motor housing envelopes at least a portion of the electric motor and the actuator brake;
an electric connector extending from the second end of the motor;
a plurality of actuator brake power conductors extending through the motor to the electric connector, the actuator brake power conductors being configured to couple to a direct current (DC) electric power source; and
a plurality of electrically conductive pins extending from the actuator brake and removably connected to the electric connector.

12. The aircraft electric brake actuator assembly of claim 1 , wherein the mounting bolt comprises an actuator brake mounting bolt, the assembly further comprising a motor mounting bolt, wherein the actuator housing comprises a mounting flange, and the motor is removably coupled to the mounting flange via the motor mounting bolt.

13. The aircraft electric brake actuator assembly of claim 1 , further comprising a bolt, wherein the motor housing is removably coupled to the actuator housing via the bolt.

14. The aircraft electric brake actuator assembly of claim 8 , further comprising a motor mounting bolt and an actuator brake mounting bolt, wherein the actuator housing comprises a mounting flange and the motor is removably coupled to the mounting flange via the motor mounting bolt, and wherein the actuator brake is removably coupled to the motor via the actuator brake mounting bolt.

15. The aircraft electric brake actuator assembly of claim 8 , further comprising a bolt, wherein the motor housing is removably coupled to the actuator housing via the bolt.

16. The aircraft electric brake actuator assembly of claim 11 , further comprising a motor mounting bolt and an actuator brake mounting bolt, wherein the actuator housing comprises a mounting flange and the motor is removably coupled to the mounting flange via the motor mounting bolt, and wherein the actuator brake is removably coupled to the motor via the actuator brake mounting bolt.

17. The aircraft electric brake actuator assembly of claim 11 , f

Assignees

• Hanlon Casey
• Geck Kellan
• Quitmeyer James Neil
• Honeywell Int Inc

Inventors

• Hanlon Casey
• Geck Kellan
• Quitmeyer James Neil

Classifications

• B60T13/746

  and mechanical transmission of the braking action · CPC title

• B60T7/042 Primary

  by electrical means, e.g. using travel or force sensors · CPC title

• F16D2125/40

  Screw-and-nut · CPC title

• B60T8/00

  Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force (by changing number of effective brake cylinders in power brake systems B60T17/10) · CPC title

• F16D65/18

  adapted for drawing members together {, e.g. for disc brakes} · CPC title