Aircraft hydraulic valve

Patent metadata

Field	Value
Publication number	US-10059434-B2
Application number	US-201514870938-A
Country	US
Kind code	B2
Filing date	Sep 30, 2015
Priority date	Oct 1, 2014
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

An aircraft hydraulic valve includes a housing, a check valve, a valve opening component, and an auxiliary hydraulic pressure supply mechanism. The housing includes a first port communicated with a first chamber of a hydraulic actuator, a second port communicated with a switch valve bypass-communicating a second chamber of the hydraulic actuator with the first chamber, and an oil channel connecting the first and second ports. The check valve interrupts oil flow from the first port to the second port. The valve opening component is configured to open the check valve with pilot pressure supplied from the second chamber. The auxiliary hydraulic pressure supply mechanism obtains hydraulic pressure, for opening the check valve, from a closed hydraulic pressure section, which is defined in the oil channel between the check valve and the first port.

First claim

The invention claimed is:

1. An aircraft hydraulic valve operatively connected with a hydraulic actuator that is configured to drive a flight control surface, the hydraulic actuator comprising a first hydraulic chamber and a second hydraulic chamber, the aircraft hydraulic valve comprising:
a housing comprising:
a first port configured to communicate with the second hydraulic chamber of the hydraulic actuator that drives the flight control surface,
a second port configured to communicate with a switch valve capable of communicating the first hydraulic chamber of the hydraulic actuator with the second hydraulic chamber of the hydraulic actuator via a bypass of the switch valve,
an oil channel configured to connect the first port and the second port,
a third port configured to communicate with a first electromagnetic valve;
a fourth port configured to communicate with a second electromagnetic valve; and
a fifth port configured to communicate with a reservoir;

a check valve configured to interrupt a flow of oil from the first port to the second port in the oil channel of the housing;
a valve opening component configured to open the check valve with pilot pressure supplied from the second hydraulic chamber of the hydraulic actuator; and
an auxiliary hydraulic pressure supply mechanism configured to obtain hydraulic pressure, for opening the check valve, from a first hydraulic pressure section, wherein the first hydraulic pressure section is defined in the oil channel between the check valve and the first port,
wherein the cross-sectional passage areas of the first port and the second port are larger than those of the third port, the fourth port, and the fifth port.

2. The aircraft hydraulic valve according to claim 1 , wherein the auxiliary hydraulic pressure supply mechanism is configured to apply hydraulic pressure, obtained from the first hydraulic pressure section to the valve opening component.

3. The aircraft hydraulic valve according to claim 2 , wherein the auxiliary hydraulic pressure supply mechanism includes an auxiliary oil channel formed in the housing,
wherein the valve opening component includes a plurality of pistons, and
wherein the auxiliary oil channel communicates the first hydraulic pressure section with a cavity formed around at least one of the plurality of pistons.

4. The aircraft hydraulic valve according to claim 3 , wherein the auxiliary hydraulic pressure supply mechanism is configured to apply hydraulic pressure of the first hydraulic pressure section to at least one of the plurality of pistons.

5. The aircraft hydraulic valve according to claim 4 , wherein the valve opening component includes
a pilot driving piston that is configured to receive pilot pressure supplied from a hydraulic pressure source,
a bypass driving piston that is configured to receive hydraulic pressure supplied through the switch valve, and
an auxiliary driving piston that is configured to receive hydraulic pressure from the first hydraulic pressure section,
wherein the auxiliary hydraulic pressure supply mechanism is configured to apply hydraulic pressure of the first hydraulic pressure section to the auxiliary driving piston.

6. An aircraft hydraulic valve operatively connected with a hydraulic actuator configured to drive a flight control surface, the hydraulic actuator comprising a first hydraulic chamber and a second hydraulic chamber, the aircraft hydraulic valve comprising:
a housing that includes
a first port adapted to communicate with the second hydraulic chamber of the hydraulic actuator that drives the flight control surface,
a second port adapted to communicate with a switch valve capable of communicating the first hydraulic chamber of the hydraulic actuator with the second hydraulic chamber via a bypass, and

an oil channel that connects the first port and the second port;
a check valve that interrupts a flow of oil from the first port to the second port in the oil channel of the housing;
a valve opening component configured to open the check valve with pilot pressure supplied from the second hydraulic chamber; and
an auxiliary hydraulic pressure supply mechanism that obtains hydraulic pressure, for opening the check valve, from a first hydraulic pressure section, wherein the first hydraulic pressure section is defined in the oil channel between the check valve and the first port,
wherein the auxiliary hydraulic pressure supply mechanism is configured to apply hydraulic pressure, obtained from the first hydraulic pressure section to the valve opening component,
wherein the auxiliary hydraulic pressure supply mechanism includes an auxiliary oil channel formed in the housing,
wherein the valve opening component includes a plurality of pistons, and
wherein the auxiliary oil channel communicates the first hydraulic pressure section with a cavity formed around at least one of the plurality of pistons,
wherein the auxiliary hydraulic pressure supply mechanism is configured to apply hydraulic pressure of the first hydraulic pressure section to at least one of the plurality of pistons,
wherein the valve opening component includes a pilot driving piston, which receives pilot pressure supplied from a hydraulic pressure source, a bypass driving piston, which receives hydraulic pressure supplied through the switch valve, and an auxiliary driving piston, which receives hydraulic pressure from the first hydraulic pressure section, and
wherein the auxiliary hydraulic pressure supply mechanism is configured to apply hydraulic pressure of the first hydraulic pressure section to the auxiliary driving piston,
wherein the bypass driving piston, the auxiliary driving piston, and the pilot driving piston respectively have diameters that decrease in this order, and
wherein the bypass driving piston, the auxiliary driving piston, and the pilot driving piston are arranged to be farther from the check valve in this order.

7. The aircraft hydraulic valve according to claim 5 , wherein the check valve includes a closed-side pressure receiving surface that is configured receive pressure of the first hydraulic pressure section, and
wherein the auxiliary driving piston has a pressure receiving area that is set in accordance with an area of the closed-side pressure receiving surface of the check valve.

8. The aircraft hydraulic valve according to claim 7 , wherein the pressure receiving area of the auxiliary driving piston is set to compensate for a difference between force acting on the bypass driving piston and force acting in a direction in which the check valve closes.

9. The aircraft hydraulic valve according to claim 1 , further comprising:
a check valve bore that extends through a valve body of the check valve, wherein the check valve bore communicates the first hydraulic pressure section with a second hydraulic pressure section that is defined in the oil channel between the check valve and the second port; and
a valve configured to open and close the check valve bore.

Assignees

• Nabtesco Corp

Inventors

• Ito Koji

Classifications

• F15B13/024

  Pressure relief valves · CPC title

• B64C13/42

  having duplication or stand-by provisions · CPC title

• F15B9/10

  in which the controlling element and the servomotor each controls a separate member, these members influencing different fluid passages or the same passage · CPC title

• F15B2211/5153

  being connected to an output member and a directional control valve · CPC title

• F15B2211/3058

  having additional valves for interconnecting the fluid chambers of a double-acting actuator, e.g. for regeneration mode or for floating mode · CPC title