Aircraft hydraulic system with a dual spool valve and methods of use

Patent metadata

Field	Value
Publication number	US-10947997-B2
Application number	US-201815952641-A
Country	US
Kind code	B2
Filing date	Apr 13, 2018
Priority date	Apr 13, 2018
Publication date	Mar 16, 2021
Grant date	Mar 16, 2021

Abstract

A dual spool valve and methods of controlling hydraulic fluid that is moved to a hydraulic actuator of an aircraft. The dual spool valve may include ports to receive and discharge hydraulic fluid. The dual spool valve may also include first and second valve sections that are selectively positionable to control the flow of hydraulic fluid into and out of the actuator. One position provides for hydraulic fluid to move through closure lines. Method of controlling the dual spool valve may provide for selectively positioning the valve sections to control the flow of hydraulic fluid, and to position the valve sections to move hydraulic fluid through a closure line during certain circumstances.

First claim

What is claimed is:

1. A dual spool valve to direct hydraulic fluid to a hydraulic actuator in an aircraft, the dual spool valve comprising:
a first port to receive hydraulic fluid from a first supply line;
a second port to discharge hydraulic fluid to a return line;
a third port to receive hydraulic fluid from a second supply line;
a first valve section comprising:
a first manifold with a supply port, a return port, and an actuator port;
a first closure line that extends between the third port and the actuator; and
a first spool movable within the first manifold between a first position to allow hydraulic fluid to flow through the first valve section to and from the actuator through just the supply port, a second position to allow hydraulic fluid to flow through the first valve section to and from the actuator through just the return port, and a third position to allow hydraulic fluid to flow through the first valve section to and from the actuator through just the first closure line;

a second valve section comprising:
a second manifold with a supply port, a return port, and an actuator port;
a second closure line that extends between the third port and the actuator; and
a second spool movable within the second manifold between a first position to allow hydraulic fluid to flow through the second valve section to and from the actuator through just the supply port, a second position to allow hydraulic fluid to flow through the second valve section to and from the actuator through just the return port, and a third position to allow hydraulic fluid to flow through the second valve section to and from the actuator through just the second closure line.

2. The dual spool valve of claim 1 , wherein the first spool comprises a shaft with first and second blocks spaced apart along the shaft, the shaft extending across the first closure line in each of the first and second positions.

3. The dual spool valve of claim 2 , wherein the shaft comprises an orifice that aligns with the first closure line in the third position to allow hydraulic fluid to flow along the first closure line and through the orifice to and from the actuator.

4. The dual spool valve of claim 3 , wherein the orifice includes a smaller sectional area than the first closure line to control a flow of hydraulic fluid moving along the first closure line when the first valve section is in the third position.

5. The dual spool valve of claim 1 , further comprising a pair of first lines that extends between the first port and the supply ports of each of the first and second manifolds, the pair of first lines sharing a common section at the first port.

6. The dual spool valve of claim 5 , further comprising a pair of second lines that extends between the second port and the return ports of each of the first and second manifolds, the pair of second lines sharing a common section at the second port.

7. The dual spool valve of claim 6 , wherein the first and second closure lines are isolated from the first and second pairs of lines.

8. An assembly to position a flight control member of an aircraft, the assembly comprising:
a hydraulic actuator operatively connected to the flight control member and comprising a piston, a first chamber on a first side of the piston, and a second chamber on a second side of the piston;
a dual spool valve comprising:
a first valve section comprising:
a first manifold with a supply port, a return port, and an actuator port;
a first closure line that extends to the first chamber of the actuator; and
a first spool movable within the first manifold between a first position to allow hydraulic fluid to flow through the first valve section to and from the first chamber of the actuator through just the supply port, a second position to allow hydraulic fluid to flow through the first valve section to and from the first chamber of the actuator through just the return port, and a third position to allow hydraulic fluid to flow through the first valve section to and from the first chamber of the actuator through just the first closure line;

a second valve section comprising:
a second manifold with a supply port, a return port, and an actuator port;
a second closure line that extends to the second chamber of the actuator; and
a second spool movable within the second manifold between a first position to allow hydraulic fluid to flow through the second valve section to and from the second chamber of the actuator through just the supply port, a second position to allow hydraulic fluid to flow through the second valve section to and from the second chamber of the actuator through just the return port, and a third position to allow hydraulic fluid to flow through the second valve section to and from the second chamber of the actuator through just the second closure line.

9. The assembly of claim 8 , wherein the dual spool valve further comprises a first port to receive hydraulic fluid, a second port to discharge hydraulic fluid, and a third port to receive hydraulic fluid.

10. The assembly of claim 9 , further comprising a first supply line fluidly connected to the first port and a second supply line fluidly connected to the third port, with the second supply line supplying hydraulic fluid to the dual spool valve at a lower pressure than the first supply line.

11. The assembly of claim 9 , further comprising a return line fluidly connected to the second port to receive hydraulic fluid that is removed from each of the first and second chambers of the actuator.

12. The assembly of claim 8 , wherein the first and second spools include a common shape and size.

13. The assembly of claim 8 , wherein the first spool comprises a shaft with first and second blocks spaced apart along the shaft, the first block positioned at the supply port in the first position, the second block positioned at the return port in the second position, and the shaft extending across the first closure line in each of the first and second positions.

14. The assembly of claim 13 , wherein the shaft of the first spool comprises an orifice that is aligned with the first closure line in the third position to allow hydraulic fluid to flow along the first closure line through the orifice to and from the first chamber of the actuator.

15. The assembly of claim 14 , wherein the orifice includes a smaller sectional area than the first closure line to control a flow of hydraulic fluid moving along the first closure line when the first valve section is in the third position.

16. The assembly of claim 13 , wherein the shaft of the second valve section comprises an orifice that is aligned with the second closure line in the third position to allow hydraulic fluid to flow along the second closure line through the orifice and to and from the second chamber of the actuator.

17. The assembly of claim 9 , further comprising a pair of first lines that extends between the first port and the supply ports of each of the first and second manifolds, the pair of first lines sharing a common section at the first port.

18. The assembly of claim 17 , further comprising a pair of second lines that extends between the second port and the return ports of each of the first and second manifolds, the pair of second lines sharing a common section at the second port.

19. The assembly of claim 18 , wherein the first and second closure lines are isolated from the first and second pairs of lines.

20. A method of controlling an actuator connected to a flight control member of an aircraft, the method comprising:

Assignees

• Boeing Co

Inventors

• Fox Michael Thomas
• Howell Eric Anton
• Roach Jeffrey M

Classifications

• F15B2211/7053

  Double-acting output members · CPC title

• F15B2211/30565

  having multiple valves for a single output member, e.g. for creating higher valve function by use of multiple valves like two 2/2-valves replacing a 5/3-valve · CPC title

• F15B2211/8757

  using redundant components or assemblies · CPC title

• F15B2211/8623

  Electric supply failure · CPC title

• F15B13/044

  operated by electrically-controlled means, e.g. solenoids, torque-motors · CPC title