Hydraulic actuator force fight mitigation mechanism

• US 10,458,557 B2
• Filed: 03/16/2017
• Issued: 10/29/2019
• Est. Priority Date: 04/20/2016
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: DeFusco, David A.
• Primary Examiner(s): Sanderson, Joseph W
• Application Number:
  US15/461,142
• Publication Number:
  US 20170307090A1
• Time in Patent Office: 957 Days
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: B64C 27/605 including swash plate, spider or cam mechanisms
• CPC Class Codes: B64C 27/64 using fluid pressure, e.g. having fluid power amplification
• CPC Class Codes: F16K 11/161 only slides
• CPC Class Codes: F16K 31/082 using a electromagnet and a permanent magnet

Abstract

A control valve for a multi-stage hydraulic actuator includes a valve body defining a translation axis, a spool disposed within the valve body and movable along the translation axis, and a flange. The flange is fixed relative to the spool and has an aperture disposed externally of the valve body to removably fix the spool to a spool of a redundant control valve independently connected to the multi-stage hydraulic actuator for mitigating force fights between actuators coupled to the control valve.

Claims

1. A hydraulic actuator assembly, comprising:

a multi-stage hydraulic actuator;

a control valve assembly having first and second control valves in fluid communication with the multi-stage hydraulic actuator through independent fluid conduits, each of the first and second control valves comprising;

a valve body defining a translation axis;

a spool disposed within the valve body and movable along the translation axis; and

a flange connected to the spool and having an aperture disposed externally of the valve body, wherein the flange is fixed relative to the spool to removably fix the spool to a spool of a redundant control valve that is independently connected to the multi-stage hydraulic actuator,

wherein the valve body of the first control valve is fixed relative to the valve body of the second control valve,

wherein the flange of the first control valve overlaps the flange of the second control valve between the valve body of the first control valve and the valve body of the second control valve; and

a tandem pin seated in at least one of the aperture of the flange of the first control valve and the aperture of the flange of the second control valve, wherein the tandem pin has an engaged position and a disengaged position, the tandem pin fixing the flange of the first control valve and the second control valve relative to one another in the engaged position, the tandem pin fixed to the flange of one of the first control valve and the second control valve in the disengaged position.

2. The hydraulic actuator assembly according to claim 1, wherein the spool and the flange of each of the first and second control valves are integrally connected to one another in a unitary structure.

3. The hydraulic actuator assembly as recited in claim 1, further including a rail fixed relative to the valve body of the first control valve and the valve body of the second control valve.

4. The hydraulic actuator assembly as recited in claim 1, wherein the first control valve and the second control valve are infinitely variable directional valves.

5. The hydraulic actuator assembly as recited in claim 1, further including a solenoid or linear motor fixed to the flange of the first control valve, the solenoid or linear motor being connected to the tandem pin, the tandem pin being slideably received in the aperture of the flange of the first control valve.

6. The hydraulic actuator assembly as recited in claim 1, wherein the aperture defined in the flange of the first control valve and in the flange of the second control valve are through-holes.

7. A rotorcraft, comprising:

a flight control device;

a multi-stage hydraulic actuator operably connected to the flight control device;

a control valve assembly having first and second control valves in fluid communication with the multi-stage hydraulic actuator through independent fluid conduits, each of the first and second control valves comprising;

a valve body defining a translation axis;

a spool disposed within the valve body and movable along the translation axis; and

a flange connected to the spool and having an aperture disposed externally of the valve body, wherein the flange is fixed relative to the spool to removably fix the spool to a spool of a redundant control valve that is independently connected to the multi-stage hydraulic actuator,

wherein the valve body of the first control valve is fixed relative to the valve body of the second control valve, wherein the flange of the first control valve overlaps the flange of the second control valve between the valve body of the first control valve and the valve body of the second control valve;

a tandem pin seated in at least one of the aperture of the flange of the first control valve and the aperture of the flange of the second control valve, wherein the tandem pin has an engaged position wherein the flange of the first control valve and the flange of the second control valve are fixed relative to one another and a disengaged position where the flanges are movable relative to one another; and

a solenoid or linear motor carried by the flange of the first control valve, the solenoid or linear motor electromagnetically coupled to the tandem pin to displace the tandem pin between engaged and disengaged positions.

8. The rotorcraft according to claim 7, wherein at least one of the first control valve and the second control valve is an infinitely variable directional valve.

9. The rotorcraft according to claim 7, wherein the aperture of each of the first and second control valves is a through hole.

10. The rotorcraft according to claim 9, further including a rail fixed relative to the valve body of each of the first and second control valves and extending along the translation axis, wherein the tandem pin is coupled to the rail and translatable relatively to the rail and along the translation axis.

11. The rotorcraft according to claim 7, wherein the flange of the second control valve overlaps the flange of the first control valve along the translation axis.

12. The rotorcraft according to claim 11, wherein the tandem pin is fixed relative to both the flange of the first control valve and the flange of the second control valve in in the engaged position.

13. The rotorcraft according to claim 11, wherein the tandem pin is fixed to only one of the flange of the first control valve and the flange of the second control valve in the disengaged position.

14. The rotorcraft as recited in claim 7, wherein the first control valve and the second control valve are infinitely variable directional valves.