Augmenting flight control surface actuation system and method

• US 6,796,526 B2
• Filed: 11/25/2002
• Issued: 09/28/2004
• Est. Priority Date: 11/25/2002
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Boehringer, Wilfred Earl
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US10/303,521
• Publication Number:
  US 20040099763A1
• Time in Patent Office: 673 Days
• Field of Search: 244/78, 244/76.R, 244/75.R, 244/226, 244/227, 915/09--14, 915/16--19, 915/21--32, 607/11, 607/16
• US Class Current: 244/78.1
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: F15B 11/036 by means of servomotors having a plurality of working chambers
• CPC Class Codes: F15B 11/161 with sensing of servomotor demand or load
• CPC Class Codes: F15B 18/00 Parallel arrangements of independent servomotor systems
• CPC Class Codes: F15B 2211/20546 variable capacity
• CPC Class Codes: F15B 2211/30505 Non-return valves, i.e. check valves
• CPC Class Codes: F15B 2211/30525 Directional control valves, e.g. 4/3-directional control valve
• CPC Class Codes: F15B 2211/3056 Assemblies of multiple valves
• CPC Class Codes: F15B 2211/31588 having a single pressure source and multiple output members
• CPC Class Codes: F15B 2211/329 actuated by fluid pressure
• CPC Class Codes: F15B 2211/50518 using pressure relief valves
• CPC Class Codes: F15B 2211/5154 being connected to multiple ports of an output member
• CPC Class Codes: F15B 2211/528 actuated by fluid pressure
• CPC Class Codes: F15B 2211/7054 Having equal piston areas
• CPC Class Codes: F15B 2211/7107 the output members being mechanically linked
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Apparatus for providing actuation power to an aircraft flight control surface. The apparatus includes a first actuator and a second actuator, where the second actuator has a bypass mode and an assist mode. The mode of the second actuator is determined by a load on the first actuator. When the second actuator is in the bypass mode, the first actuator provides the actuation power for the aircraft flight control surface. But, when the second actuator is in the assist mode, both the first and second actuators provide the actuation power for the aircraft flight control surface. Accordingly, the apparatus allows the flight control surface to be operated in a more efficient manner with less hydraulic flow being required.

Claims

1. Apparatus for providing actuation power to an aircraft flight control surface, the apparatus comprising:

a first actuator;

a second actuator including a bypass mode and an assist mode, the mode of the second actuator being at least partially based on a load of the first actuator;

the second actuator being in the bypass mode during a low load operating condition such that the first actuator provides the actuation power for the aircraft flight control surface when the second actuator is in the bypass mode during said low load operating condition; and

the second actuator being in the assist mode during a high load operating condition such that the first and second actuators provide the actuation power for the aircraft flight control surface when the second actuator is in the assist mode during said high load operating condition.

3. The apparatus of claim 1, wherein the assist mode comprises a default mode for the second actuator.

4. The apparatus of claim 1, further comprising a bypass valve for selecting between the bypass mode and the assist mode for the second actuator.

5. The apparatus of claim 4, further comprising at least one differential trigger valve operatively associated with the bypass valve such that triggering the at least one differential trigger valve causes the bypass valve to select the other one of said modes for the second actuator, the at least one differential trigger valve being triggered when an internal differential pressure across the first actuator exceeds a maximum pressure value.

6. The apparatus of claim 5, wherein the at least one differential trigger valve comprises:

a first differential trigger valve disposed to trigger when the internal pressure differential across the first actuator for retracting the aircraft flight control surface exceeds a maximum pressure value; and

a second differential trigger valve disposed to trigger when the internal pressure differential across the first actuator for extending the aircraft flight control surface exceeds a maximum pressure value.

10. The apparatus of claim 1, wherein the first actuator comprises a plurality of actuators.

11. The apparatus of claim 1, wherein the second actuator comprises a plurality of actuators.

2. Apparatus for providing actuation power to an aircraft flight control surface, the apparatus comprising:

a first actuator;

a second actuator including a bypass mode and an assist mode, the mode of the second actuator being at least partially based on a load of the first actuator;

the first actuator providing the actuation power for the aircraft flight control surface when the second actuator is in the bypass mode;

the first and second actuators providing the actuation power for the aircraft flight control surface when the second actuator is in the assist mode; and

wherein the bypass mode comprises a default mode for the second actuator.

7. Apparatus for providing actuation power to an aircraft flight control surface, the apparatus comprising:

a first actuator;

a second actuator including a bypass mode and an assist mode, the mode of the second actuator being at least partially based on a load of the first actuator;

the first actuator providing the actuation power for the aircraft flight control surface when the second actuator is in the bypass mode;

the first and second actuators providing the actuation power for the aircraft flight control surface when the second actuator is in the assist mode; and

at least one triggered balance relief valve for selecting between the bypass mode and the assist mode for the second actuator, the at least one triggered balance relief valve selecting the other one of said modes for the second actuator when the at least one triggered balance relief valve is triggered, the at least one triggered balance relief valve being triggered when a pressure upstream of the at least one triggered balance relief valve exceeds a maximum pressure value.

8. The apparatus of claim 7, wherein the at least one triggered balance relief valve comprises:

a first triggered balance relief valve disposed within an extend fluid line of the second actuator; and

a second triggered balance relief valve disposed within a retract fluid line of the second actuator.

9. The apparatus of claim 7, further comprising at least one anti-cavitation check valve in fluid communication with the second actuator.

12. Apparatus for providing actuation power to an aircraft flight control surface, the apparatus comprising:

a first actuator;

a second actuator including a bypass mode and an assist mode;

means for selecting between the bypass mode and the assist mode for the second actuator, the mode selection for the second actuator being at least partially based on a load of the first actuator;

the second actuator being in the bypass mode during a low load operating condition such that the first actuator provides the actuation power for the aircraft flight control surface when the second actuator is in the bypass mode during said low load operating condition; and

the second actuator being in the assist mode during a high load operating condition such that the first and second actuators provide the actuation power for the aircraft flight control surface when the second actuator is in the assist mode during said high load operating condition.

13. An aircraft comprising:

a flight control surface;

a first actuator;

a second actuator including a bypass mode and an assist mode, the mode of the second actuator being at least partially based on a load of the first actuator;

the second actuator being in the bypass mode during a low load operating condition such that the first actuator provides the actuation power for the aircraft flight control surface when the second actuator is in the bypass mode during said low load operating condition; and

the second actuator being in the assist mode during a high load operating condition such that the first and second actuators provide the actuation power for the aircraft flight control surface when the second actuator is in the assist mode during said high load operating condition.

14. The aircraft of claim 13, further comprising a bypass valve for selecting between the bypass mode and the assist mode for the second actuator.

15. The aircraft of claim 13, further comprising at least one differential trigger valve operatively associated with the bypass valve such that triggering the at least one differential trigger valve causes the bypass valve to select the other one of said modes for the second actuator, the at least one differential trigger valve being triggered when an internal differential pressure across the first actuator exceeds a maximum pressure value.

16. The aircraft of claim 15, wherein the at least one differential trigger valve comprises:

a first differential trigger valve disposed to trigger when the internal pressure differential across the first actuator for retracting the aircraft flight control surface exceeds a maximum pressure value; and

a second differential trigger valve disposed to trigger when the internal pressure differential across the first actuator for extending the aircraft flight control surface exceeds a maximum pressure value.

20. The aircraft of claim 13, wherein the first actuator comprises a plurality of actuators.

21. The aircraft of claim 13, wherein the second actuator comprises a plurality of actuators.

17. An aircraft comprising:

a flight control surface;

a first actuator;

a second actuator including a bypass mode and an assist mode, the mode of the second actuator being at least partially based on a load of the first actuator;

the first actuator providing actuation power for the flight control surface when the second actuator is in the bypass mode;

the first and second actuators providing actuation power for the flight control surface when the second actuator is in the assist mode; and

at least one triggered balance relief valve for selecting between the bypass mode and the assist mode for the second actuator, the at least one triggered balance relief valve selecting the other one of said modes for the second actuator when the at least one triggered balance relief valve is triggered, the at least one triggered balance relief valve being triggered when a pressure upstream of the at least one triggered balance relief valve exceeds a maximum pressure value.

18. The aircraft of claim 17, wherein the at least one triggered balance relief valve comprises:

a first triggered balance relief valve disposed within an extend fluid line of the second actuator; and

a second triggered balance relief valve disposed within a retract fluid line of the second actuator.

19. The aircraft of claim 17, further comprising at least one anti-cavitation check valve in fluid communication with the second actuator.

22. A method of providing actuation power to an aircraft flight control surface, the method comprising:

selecting between a bypass mode and an assist mode for a second actuator, the selection being at least partially based on a load of a first actuator;

using the first actuator to provide the actuation power for the aircraft flight control surface when the second actuator is in the bypass mode during a low load operation condition; and

using the first and second actuators to provide the actuation power for the aircraft flight control surface when the second actuator is in the assist mode during a high load operating condition.

23. The method of claim 22, wherein selecting between a bypass mode and an assist mode for a second actuator comprises:

selecting the assist mode when an internal differential pressure across the first actuator exceeds a maximum pressure value; and

selecting the bypass mode when the internal differential pressure across the first actuator falls below a minimum pressure value.

24. The method of claim 22, wherein selecting between a bypass mode and an assist mode for a second actuator comprises:

selecting the assist mode when a pressure upstream of the first actuator exceeds a maximum pressure value; and

selecting the bypass mode when the pressure upstream of the first actuator falls below a minimum pressure value.