Electrically controlled park and emergency valve assembly

Patent metadata

Field	Value
Publication number	US-10259571-B2
Application number	US-201615388420-A
Country	US
Kind code	B2
Filing date	Dec 22, 2016
Priority date	Dec 6, 2016
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

An electrically controlled park and emergency brake system is disclosed. The brake system may comprise a brake control module having a shut-off valve in fluid communication with an outboard servo-valve and an inboard servo-valve. An emergency/park power source may supply fluid to the shut-off valve. The brake system may also comprise a vehicle management system in electronic communication with the brake control module. The brake system may also comprise mechanical inputs, including a wheel well brake handle and a cockpit brake handle. The brake system may also comprise redundant emergency/park power sources.

First claim

What is claimed is:

1. An aircraft brake system, comprising:
a brake control module comprising:
a shut-off valve (SOV) to release a first fluid in response to at least one of a first power signal or a second power signal;
an outboard servo-valve (OBSV) in fluid communication with the SOV via a first fluid conduit in response to the SOV being in an open position and in fluid communication via a first outboard (OB) fluid conduit with at least one of a right outboard shuttle valve (ROBSV) or a left outboard shuttle valve (LOBSV); and
an inboard servo-valve (IBSV) in fluid communication with the SOV via the first fluid conduit in response to the SOV being in an open position and in fluid communication via a first inboard (IB) fluid conduit with and at least one of a right inboard shuttle valve (RIBSV) or a left inboard shuttle valve (LIBSV);

an emergency/park power source in fluid communication with the SOV;
a vehicle management system (VMS) in electronic communication with the brake control module,
wherein the brake control module is configured to receive a signal comprising at least one of a VMS signal, a park value, or an emergency value, wherein in response to receiving the signal, at least one of the OBSV or the IBSV may be configured to at least partially open;
a cockpit brake handle in mechanical communication with a control valve, wherein the control valve is in fluid communication with at least one of the ROBSV or the LOBSV via a second outboard (OB) fluid conduit in response to the control valve being in an open position, wherein the control valve is in fluid communication with at least one of the RIBSV or the LIBSV via a second inboard (IB) fluid conduit, and wherein the control valve is configured to release a second fluid into the second OB fluid conduit and the second IB fluid conduit in response to the cockpit brake handle being activated; and
a wheel well brake handle in mechanical communication with the control valve, wherein the control valve is configured to release the second fluid into the second OB fluid conduit and the second IB fluid conduit in response to the wheel well brake handle being activated.

2. The aircraft brake system of claim 1 , further comprising a plurality of switches in communication with the brake control module, wherein the plurality of switches comprises at least one of a cockpit enable switch, a wheel well enable switch, a VMS enable switch, a wheel well park switch, a cockpit park switch, or an emergency activate switch.

3. The aircraft brake system of claim 2 , wherein the SOV is configured to receive the at least one of the first power signal or the second power signal in response to at least one of the cockpit enable switch, the wheel well enable switch, or the VMS enable switch being switched on.

4. The aircraft brake system of claim 1 , wherein the IBSV and the OBSV are configured to meter a flow of the fluid supplied by the SOV according to at least one of the park value, the emergency value, or the VMS signal.

5. The aircraft brake system of claim 1 , further comprising an outboard braking system in fluid communication with at least one of the ROBSV or the LOBSV and an inboard braking system in fluid communication with at least one of the RIBSV or the LIBSV.

6. The aircraft brake system of claim 5 , wherein the ROBSV, the LOBSV, the RIBSV, and the LIBSV are configured to meter a flow of a plurality of fluids according to a pressure of the plurality of fluids.

7. The aircraft brake system of claim 1 , further comprising:
a third inboard (IB) shuttle valve in fluid communication with the IBSV via the first IB fluid conduit in response to the IBSV being in an open position, and the third IB shuttle valve being in fluid communication via with the control valve via the second IB fluid conduit in response to the control valve being in an open position, wherein the third IB shuttle valve is configured to output either a first IB input pressure from the first IB fluid conduit or a second IB pressure from the second IB fluid conduit in response to both the IBSV and the control valve being in an open position; and
a third outboard (OB) shuttle valve in fluid communication with the OBSV via the first OB fluid conduit in response to the OBSV being in an open position, and the third OB shuttle valve being in fluid communication via the control valve via the second OB fluid conduit in response to the control valve being in an open position, wherein the third OB shuttle valve are configured to output either a first OB input pressure from the first OB fluid conduit or a second OB pressure from the second OB fluid conduit in response to both the OBSV and the control valve being in an open position.

8. A redundant emergency/park power source brake system, comprising:
a first brake control module, comprising:
a first shut-off valve (SOV) configured to release a first fluid in response to at least one of a first power signal or a second power signal; and
an outboard servo-valve (OBSV) in fluid communication with the first SOV via a first fluid conduit in response to the first SOV being in an open position and in fluid communication via a first outboard (OB) fluid conduit with at least one of a right outboard shuttle valve (ROBSV) or a left outboard shuttle valve (LOBSV);

a second brake control module, comprising:
a second SOV configured release a second fluid in response to at least one of the first power signal or the second power signal; and
an inboard servo-valve (IBSV) in fluid communication with the second SOV via a second fluid conduit in response to the second SOV being in an open position and in fluid communication via a first inboard (IB) fluid conduit with and at least one of a right inboard shuttle valve (RIBSV) or a left inboard shuttle valve (LIBSV);

a first emergency/park power source in fluid communication with the first SOV;
a second emergency/park power source in fluid communication with the second SOV; and
a vehicle management system (VMS) in electronic communication with the first brake control module and the second brake control module,
wherein the first brake control module is configured to receive a first signal comprising at least one of a VMS signal, a park value, or an emergency value, wherein in response to receiving the signal, the OBSV is configured to at least partially open,
wherein the second brake control module is configured to receive a second signal comprising at least one of the VMS signal, the park value, or the emergency value, wherein in response to receiving the signal, the IBSV is configured to at least partially open; and
a cockpit brake handle in mechanical communication with a control valve, wherein the control valve is in fluid communication with at least one of the ROBSV or the LOBSV via a second outboard (OB) fluid conduit in response to the control valve being in an open position, wherein the control valve is in fluid communication with at least one of the RIBSV or the LIBSV via a second inboard (IB) fluid conduit, and wherein the control valve is configured to release a third fluid into the second OB fluid conduit and the second IB fluid conduit in response to the cockpit brake handle being activated; and
a wheel well brake handle in mechanical communication with the control valve, wherein the control valve is configured to release the second fluid into the second OB fluid conduit and the second IB fluid conduit in response to the wheel well brake handle being activated.

9. The redundant emergency/park power source brake system of claim 8 , further comprising a plurality of switches in communication with the first brake control module and the second brake control module, wherein the plurality of switches comprises at least one of a cockpit e

Assignees

• Goodrich Corp

Inventors

• Cahill Eric Daniel
• Burte Paul R
• Canan Casey
• Ayichew Efrem E
• Stein David B

Classifications

• B64C25/46

  Brake regulators for preventing skidding or aircraft somersaulting · CPC title

• B60T15/028

  in hydraulic systems · CPC title

• B64C25/44 Primary

  Actuating mechanisms · CPC title

• B60T8/1703 Primary

  for aircrafts · CPC title

• B64C25/42

  Arrangement or adaptation of brakes · CPC title