Apparatus and method for controlling a hydraulic brake of an aircraft

Patent metadata

Field	Value
Publication number	US-9376096-B2
Application number	US-201414460651-A
Country	US
Kind code	B2
Filing date	Aug 15, 2014
Priority date	Aug 15, 2014
Publication date	Jun 28, 2016
Grant date	Jun 28, 2016

Abstract

An apparatus for controlling a hydraulically-actuated brake of an aircraft includes a brake control unit. The brake control unit is configured to receive a brake signal from an operator of the aircraft. A pump is in fluidic communication with a reservoir for holding hydraulic fluid and the brake for supplying the hydraulic fluid from the reservoir to the brake. An electric motor is in communication with the brake control unit and coupled to the pump to control pressure of the hydraulic fluid supplied by the pump in accordance with the brake signal.

First claim

What is claimed is:

1. An apparatus for controlling a hydraulically-actuated brake of an aircraft, said apparatus comprising:
a brake control unit configured to receive a brake signal corresponding to actuation of a brake control input device from an operator of the aircraft;
a reservoir for holding hydraulic fluid;
a pump in fluidic communication with said reservoir and the brake and configured to supply the hydraulic fluid from said reservoir to the brake; and
an electric motor in communication with said brake control unit and coupled to said pump to control pressure of the hydraulic fluid in accordance with the brake signal,
wherein the aircraft includes a hydraulic system providing hydraulic fluid, said apparatus further comprising a source selection valve in fluidic communication with the hydraulic system, said pump, and the brake and configured to select hydraulic fluid from one of the hydraulic system and said pump and supply the hydraulic fluid to the brake, and
wherein the apparatus further comprises a pressure sensing device configured to sense a pressure of the hydraulic system and in communication with said source selection valve and wherein said source selection valve is configured to select hydraulic fluid from said pump and deliver the hydraulic fluid to the brake in response to a pressure of the hydraulic system being less than a predetermined value.

2. The apparatus as set forth in claim 1 , further comprising a brake control valve in communication with said brake control unit and disposed fluidically between the hydraulic system and said source selection valve to control pressure of the hydraulic fluid in accordance with the brake signal.

3. The apparatus as set forth in claim 1 , further comprising a motor control device in communication with said brake control unit and said electric motor and configured to receive a brake control unit signal from said brake control unit corresponding to the brake signal and control said electric motor in accordance with said brake control unit signal.

4. An aircraft comprising:
a hydraulically-actuated brake,
a brake control unit configured to receive a brake signal corresponding to actuation of a brake control input device from an operator of said aircraft;
a reservoir for holding hydraulic fluid;
a pump in fluidic communication with said reservoir and said brake and configured to supply the hydraulic fluid from said reservoir to said brake;
an electric motor in communication with said brake control unit and coupled to said pump to control pressure of the hydraulic fluid in accordance with the brake signal;
a hydraulic system providing hydraulic fluid;
a source selection valve in fluidic communication with said hydraulic system, said pump, and said brake and configured to select hydraulic fluid from one of said hydraulic system and said pump and supply the hydraulic fluid to the brake; and
a pressure sensing device in communication with said source selection valve and configured to sense a pressure of said hydraulic system,
wherein said source selection valve is configured to select hydraulic fluid from said pump and supply the hydraulic fluid from said pump to said brake in response to a pressure of said hydraulic system being less than a predetermined value.

5. The aircraft as set forth in claim 4 , further comprising a brake control valve in communication with said brake control unit and disposed fluidically between said hydraulic system and said source selection valve to control pressure of the hydraulic fluid in accordance with the brake signal.

6. The aircraft as set forth in claim 4 , further comprising a motor control device in communication with said brake control unit and said electric motor and configured to receive a brake control unit signal from said brake control unit corresponding to the brake signal and control said electric motor in accordance with said brake control unit signal.

7. The aircraft as set forth in claim 4 , wherein
said brake comprises a left outboard brake, a left inboard brake, a right inboard brake, and a right outboard brake;
said reservoir comprises a first reservoir and a second reservoir;
said electric motor comprises a first electric motor and a second electric motor;
said pump comprises
a first pump coupled to said first electric motor and in fluidic communication with said first reservoir, said left outboard brake, and said right outboard brake to supply the hydraulic fluid from said first reservoir to said outboard brakes, and
a second pump coupled to said second electric motor and in fluidic communication with said second reservoir, said left inboard brake, and said right inboard brake to supply the hydraulic fluid from said second reservoir to said inboard brakes.

8. A method of controlling a hydraulically-actuated brake of an aircraft, the method comprising:
receiving a brake signal corresponding to actuation of a brake control input device from an operator of the aircraft at a brake control unit;
transmitting a brake control command signal corresponding to the brake signal from the brake control unit;
supplying hydraulic fluid from a reservoir to the brake with a pump;
controlling pressure of the hydraulic fluid with an electric motor coupled to the pump disposed between the reservoir and the brake in accordance with the brake control command signal; and
sensing a pressure of the hydraulic system.

9. The method as set forth in claim 8 , further comprising selecting hydraulic fluid from either the pump or a hydraulic system of the aircraft with a source selection valve and supplying the hydraulic fluid to the brake.

10. The method as set forth in claim 8 , further comprising selecting hydraulic fluid from the pump in response to a pressure of the hydraulic system being less than a predetermined value.

11. The method as set forth in claim 8 , further comprising controlling pressure of the hydraulic fluid of the hydraulic system with a brake control valve in communication with the brake control unit in accordance with the brake signal.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Knight Michael

Classifications

• B60T13/14 Primary

  using accumulators or reservoirs {fed by pumps} · CPC title

• B64C25/44

  Actuating mechanisms · CPC title

• B60T13/686

  in hydraulic systems or parts thereof · CPC title

• B60T13/662

  characterised by specified functions of the control system components · CPC title

• F15B20/004

  Fluid pressure supply failure · CPC title