# US 2008/0185476 A1 · Dual Motor Dual Concentric Valve

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- Number: US 2008/0185476 A1
- Document ID: US20080185476A1
- Status: Published application
- Kind: A1
- Application number: 11/814,923
- Filed: 2005-06-27
- Published: 2008-08-07
- Earliest claimed: 2005-02-11
- Assignees: Bell Helicopter Textron Inc.
- Inventors: Brian Suisse; Carlos A. Fenny; Kim Coakley; George Alagozian
- Web page: https://patentgrep.com/patent/US20080185476A1

## CPC

- B64C 13/505: {having duplication or stand-by provisions}
- F15B 18/00: Parallel arrangements of independent servomotor systems
- B64C 27/605: including swash plate, spider or cam mechanisms
- F15B 20/008: {Valve failure}
- F15B 2211/8636: Circuit failure, e.g. valve or hose failure
- F15B 2211/864: Failure of an output member, e.g. actuator or motor failure
- F15B 2211/8757: using redundant components or assemblies
- Y10T 137/6906: Aerial or water-supported [e.g., airplane or ship, etc.]
- Y10T 137/86493: Multi-way valve unit
- Y10T 137/86582: Pilot-actuated
- Y10T 137/86622: Motor-operated
- B64C: AEROPLANES; HELICOPTERS
- F15B: SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

An actuator control system has a dual concentric servo valve having a spool and at least one motor adapted to selectively displace the spool.

## Claims

### Claim 1

An actuator control system comprising:
a dual concentric servo valve having a tandem spool; and
at least one motor coupled to the spool for selectively displacing the spool.

### Claim 2 (depends on 1)

The actuator control system according to claim 1, further comprising:
a computer for controlling the at least one motor.

### Claim 3 (depends on 1)

The actuator control system according to claim 1, wherein the dual concentric servo valve is adapted to be powered by at least two hydraulic pumping systems.

### Claim 4 (depends on 1)

The actuator control system according to claim 1, further comprising:
at least one rotary variable differential transformer for sensing the location of the spool.

### Claim 5 (depends on 1)

The actuator control system according to claim 1, wherein the dual concentric servo valve is adapted to control a flight control output device.

### Claim 6 (depends on 5)

The actuator control system according to claim 5, wherein the flight control output device is a set of rotor blades of a rotorcraft.

### Claim 7 (depends on 1)

The actuator control system according to claim 1, wherein the motor is a torque motor.

### Claim 8 (depends on 1)

The actuator control system according to claim 1, further comprising:
a dual piston actuator coupled to the dual concentric servo valve.

### Claim 9 (depends on 8)

The actuator control system according to claim 8, wherein the dual piston actuator is a parallel dual piston actuator.

### Claim 10 (depends on 8)

The actuator control system according to claim 8, wherein the dual piston actuator is a tandem dual piston actuator.

### Claim 11 (depends on 8)

The actuator control system according to claim 8, further comprising:
a linear variable differential transformer for sensing the location of the dual piston actuator.

### Claim 12 (depends on 1)

The actuator control system according to claim 1, wherein the at least one motor comprises:
a first motor coupled to one end of the spool; and
a second motor coupled to and opposing end of the spool.

### Claim 13

A flight control system comprising:
a flight control computer adapted to receive a pilot input;
at least one motor conductively coupled to the flight control computer; and
a dual concentric servo valve having a tandem spool, the spool being coupled to the at least one motor, such that the spool may be selectively actuated by the flight control computer.

### Claim 14 (depends on 13)

The flight control system according to claim 13, wherein the at least one motor is a torque motor.

### Claim 15 (depends on 13)

The flight control system according to claim 13, wherein the at least one motor comprises:
a first motor coupled to one end of the spool; and
a second motor coupled to and opposing end of the spool.

### Claim 16 (depends on 13)

The flight control system according to claim 13, further comprising:
an actuator coupled to the dual concentric servo valve.

### Claim 17 (depends on 16)

The flight control system according to claim 16, further comprising:
a linear variable differential transformer for sensing the location of the actuator.

### Claim 18 (depends on 13)

The flight control system according to claim 13, further comprising:
a rotary variable differential transformer for sensing the location of the spool.

### Claim 19

A method of controlling an actuator, comprising the steps of:
providing a dual concentric servo valve having a tandem spool;
coupling at least one motor to the tandem spool;
coupling the dual concentric servo valve to the actuator;
controlling the actuator by selectively driving the motor.

### Claim 20 (depends on 19)

The method according to claim 19, further comprising the steps of:
providing at least one sensor for sensing the position of the spool; and
sensing the position of the spool with the sensor.