Actuator systems with shared redundancy

Patent metadata

Field	Value
Publication number	US-12024306-B2
Application number	US-202217581525-A
Country	US
Kind code	B2
Filing date	Jan 21, 2022
Priority date	Jan 21, 2022
Publication date	Jul 2, 2024
Grant date	Jul 2, 2024

Abstract

An actuator system can include a first actuator, a second actuator, a first actuator control device configured to control the first actuator, a second actuator control device configured to control the second actuator, a shared redundant actuator control device, and at least one transfer device operatively connected to the first, second, and shared redundant actuator control devices. The at least one transfer device can be configured to be operated to select between a first control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, a second control mode where the shared redundant actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, and a third control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the shared redundant actuator control device is operatively connected to the second actuator to control the second actuator.

First claim

What is claimed is:

1. An actuator system, comprising:
a first actuator;
a second actuator;
a first actuator control device configured to control the first actuator;
a second actuator control device configured to control the second actuator;
a shared redundant actuator control device; and
at least one transfer device operatively connected to the first, second, and shared redundant actuator control devices and configured to be operated to select between:
a first control mode wherein the first actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator;
a second control mode wherein the shared redundant actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator; and
a third control mode wherein the first actuator control device is operatively connected to the first actuator to control the first actuator and the shared redundant actuator control device is operatively connected to the second actuator to control the second actuator,

wherein the first actuator and the second actuator are hydraulic actuators, wherein the first actuator control device, the second actuator control device and the shared redundant actuator control device are electrohydraulic servo valves (EHSVs) configured to control a position of the first actuator and/or second actuator as a function of a respective actuator valve control pressures and electrical inputs when connected to a respective actuator.

2. The system of claim 1 , wherein each actuator control device is operatively connected to a supply pressure line having a supply pressure and a return pressure line having a return pressure.

3. The system of claim 2 , wherein each actuator control device is configured to output a first control pressure on a first control line and a second control pressure on a second control line to a respective actuator when connected to the respective actuator.

4. The system of claim 3 , wherein the at least one transfer valve is a single transfer valve.

5. The system of claim 4 , further comprising a transfer valve control device configured to control the position of the single transfer valve.

6. The system of claim 5 , wherein the transfer valve control device is an EHSV configured to control a position of the transfer valve as a function of a first transfer valve control pressure on a first transfer control line and a second transfer valve control pressure on a second transfer control line.

7. The system of claim 2 , wherein the at least one transfer valve includes a first transfer valve configured to select between the first actuator control device and the shared redundant actuator control device to be connected to the first actuator, and a second transfer valve configured to select between the second actuator control device and the shared redundant actuator control device to be connected to the second actuator.

8. The system of claim 7 , further comprising a first transfer valve control device configured to control the position of the first transfer valve, and a second transfer valve control device configured to control the position of the second transfer valve.

9. The system of claim 8 , wherein the first transfer valve control device includes a first solenoid valve connected to the first transfer valve to supply a first transfer control pressure to the first transfer valve on a first side thereof.

10. The system of claim 9 , wherein the second transfer valve control device includes a second solenoid valve connected to the second transfer valve to supply a second transfer control pressure to the second transfer valve on a first side thereof.

11. The system of claim 10 , wherein the first transfer valve and the second transfer valve are connected to a common return pressure line on a respective second side thereof.

12. An aircraft actuator system, comprising:
two actuators including a first actuator and a second actuator; and
three control valves configured to provide primary control and redundant control for the two actuators, the three control valves including, a first actuator control device configured to control the first actuator, a second actuator control device configured to control the second actuator, a shared redundant actuator control device; and
at least one transfer device operatively connected to the first, second, and shared redundant actuator control devices and configured to be operated to select between:
a first control mode wherein the first actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator;
a second control mode wherein the shared redundant actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator; and
a third control mode wherein the first actuator control device is operatively connected to the first actuator to control the first actuator and the shared redundant actuator control device is operatively connected to the second actuator to control the second actuator,

wherein the first actuator and the second actuator are hydraulic actuators, wherein the first actuator control device, the second actuator control device and the shared redundant actuator control device are electrohydraulic servo valves (EHSVs) configured to control a position of the first actuator and/or second actuator as a function of a respective actuator valve control pressures and electrical inputs when connected to a respective actuator.

13. The system of claim 12 , wherein each actuator control device is operatively connected to a supply pressure line having a supply pressure and a return pressure line having a return pressure.

14. A method, comprising:
using a first actuator control device, a second actuator control device, and a shared redundant actuator control device to provide backup redundant control to a first actuator and a second actuator on an aircraft, the first actuator control device configured to control the first actuator, the second actuator control device configured to control the second actuator; and
wherein the first actuator control device, the second actuator control device and the shared redundant actuator control device are electrohydraulic servo valves (EHSVs) configured to control a position of the first actuator and/or second actuator as a function of a respective actuator valve control pressures and electrical inputs when connected to a respective actuator.

15. The method of claim 14 , further comprising switching which actuator is connected to the single shared redundant actuator control device.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Susca Ryan
• Marocchini Francis P
• Ballard Peter M

Classifications

• F15B20/008 Primary

  Valve failure · CPC title

• G05D16/204

  the plurality of throttling means being arranged in parallel · CPC title

• G05D16/2022

  actuated by a proportional solenoid (throttling means G05D16/2024) · CPC title

• F15B11/16

  with two or more servomotors · CPC title

• F15B18/00

  Parallel arrangements of independent servomotor systems · CPC title