Aircraft control surface drive system and associated methods

• US 7,913,955 B2
• Filed: 03/23/2009
• Issued: 03/29/2011
• Est. Priority Date: 11/24/2003
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Jones, Kelly T.
• Primary Examiner(s): Dinh; Tien
• Application Number:
  US12/409,460
• Publication Number:
  US 20090308983A1
• Time in Patent Office: 736 Days
• Field of Search: 244/226, 244/78.1, 244211-213
• US Class Current: 244/226
• CPC Class Codes: B64C 13/42 having duplication or stand-by provisions
• CPC Class Codes: B64D 2045/001 for indicating symmetry of flaps deflection
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 137/87161 With common valve operator
• CPC Class Codes: Y10T 29/4933 Fluid coupling device

Abstract

A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims (37 C.F.R. §1.72(b)).

Claims

1. A control surface drive system for moving an aircraft control surface, the system being coupleable to a source of hydraulic fluid, comprising:

first and second supply lines and a return line coupleable to the source of hydraulic fluid;

an actuator assembly coupled to the first and second supply lines and to the return line, the actuator assembly having;

a hydraulic actuator connectable to the aircraft control surface and being movable between first and second positions, the hydraulic actuator configured to receive hydraulic fluid from the first supply line when the hydraulic actuator moves toward the first position, and configured to receive hydraulic fluid from the second supply line when the hydraulic actuator moves toward the second position;

a flow blocking member coupled to the first and second supply lines and being movable between an open position and a closed position, with the flow blocking member in the closed position preventing movement of the hydraulic fluid to and from the hydraulic actuator; and

a bypass line in fluid communication with the first and second supply lines and positioned to direct hydraulic fluid from one of the first and second supply lines into the other one of the first and second supply lines at a position intermediate the source and the hydraulic actuator when the hydraulic actuator moves toward the first position to recycle the hydraulic fluid back into the other one of the first and second supply lines.

2. The system of claim 1 wherein the actuator assembly includes a position sensor connected to the hydraulic actuator.

3. The system of claim 1 wherein the flow-blocking member is a valve biased toward the closed position.

4. The system of claim 1 wherein the flow blocking member is a pressure-sensitive valve.

5. The system of claim 1 wherein the actuator assembly has a valve member configured to modulate flow of hydraulic fluid to and from the hydraulic actuator.

6. The system of claim 1, further comprising a flow control assembly connected to the return line.

7. The system of claim 1, further comprising a valve connected to the bypass line to prevent backflow of the hydraulic fluid.

8. The system of claim 1 wherein the first position of the hydraulic actuator is an extended position and the second position is a retracted position, the hydraulic actuator being configured to receive hydraulic fluid from the first supply line to move toward the extended position, and configured to receive hydraulic fluid from the second supply line to move toward the retracted position.

9. The system of claim 1, further comprising an alternate mode power system coupled to the actuator assembly and dedicated for operation of the actuator assembly.

10. The system of claim 1, further comprising an alternate mode power system having a hydraulic line connected to at least one of the first and second supply lines, and a pump connected to the hydraulic line.

11. The system of claim 10 wherein the alternate mode power system includes a flow control member connected to the hydraulic line and operatively coupled to a control computer.

12. An aircraft system, comprising:

first and second control surfaces;

a source of hydraulic fluid;

a first control system coupled to the first control surface and a second control system coupled to the second control surface, each of the first and second control systems comprising;

first and second supply lines coupled to the source of hydraulic fluid;

a return line coupled to the source of hydraulic fluid;

a hydraulic actuator connected to at least one of the first and second aircraft control surfaces, the hydraulic actuator being movable between first and second positions, the hydraulic actuator configured to receive hydraulic fluid from the first supply line when the hydraulic actuator moves toward the first position, and configured to receive hydraulic fluid from the second supply line when the hydraulic actuator moves toward the second position;

a flow blocking member coupled to the first and second supply lines and being movable between an open position and a closed position, the flow blocking member in the closed position prevents movement of the hydraulic fluid to and from the hydraulic actuator; and

a bypass line in fluid communication with the first and second supply lines and positioned to direct hydraulic fluid from one of the first and second supply lines into the other one of the first and second supply lines upstream of the hydraulic actuator when the hydraulic actuator moves toward the first position to recycle the hydraulic fluid back into the other one of the first and second supply lines.

13. The aircraft system of claim 12 wherein the first aircraft control surface is a first wing flap, and the second aircraft control surface is a second wing flap.

14. The aircraft system of claim 12 wherein the at least one of the first and second control systems further includes a valve member connected to one of the first and second supply lines and being adjustable to modulate flow of hydraulic fluid to and from the hydraulic actuator.

15. The aircraft system of claim 12 wherein the first position of the hydraulic actuator is an extended position and the second position is a retracted position, the hydraulic actuator being configured to receive hydraulic fluid from the first supply line to move toward the extended position, and configured to receive hydraulic fluid from the second supply line to move toward the retracted position.

16. The aircraft system of claim 12 wherein at least one of the first and second control systems further comprises a power system coupled to the hydraulic actuator and dedicated for operation with the at least one of the first and second control systems.

17. The aircraft system of claim 12, further comprising a fuselage and a wing connected to the fuselage, at least one of the first and second control surfaces being connected to the wing.

18. A control surface drive system for moving an aircraft control surface, the system being coupleable to a source of hydraulic fluid, comprising:

first and second supply lines and a return line coupleable to the source of hydraulic fluid;

means for moving the aircraft control surface coupled to the first and second supply lines and to the return line, the means for moving the aircraft control surface having;

a means for hydraulically adjusting the control surface movable between first and second positions and configured to receive hydraulic fluid from the first supply line when the means for hydraulically adjusting the control surface moves toward the first position, and configured to receive hydraulic fluid from the second supply line when the means for hydraulically adjusting the control surface moves toward the second position;

means for blocking flow of hydraulic fluid coupled to the first and second supply lines and being movable between an open position and a closed position, with the means for blocking flow of hydraulic fluid in the closed position preventing movement of the hydraulic fluid to and from the means for hydraulically adjusting the control surface; and

a means for bypassing a portion of the hydraulic fluid in communication with the first and second supply lines and positioned to direct hydraulic fluid from one of the first and second supply lines into the other one of the first and second supply lines at a position intermediate the source and the means for hydraulically adjusting the control surface when the means for hydraulically adjusting the control surface moves toward the first position to recycle the hydraulic fluid back into the other one of the first and second supply lines.

19. The system of claim 18 wherein the means for moving the aircraft control surface includes a means for sensing the position of the means for hydraulically adjusting the control surface.

20. The system of claim 18 wherein the means for blocking flow of hydraulic fluid is a valve biased toward the closed position.

21. The system of claim 18 wherein the means for moving the aircraft control surface is adjustable to modulate flow of hydraulic fluid to and from the hydraulic actuator.

22. The system of claim 18, further comprising a valve connected to the a means for bypassing a portion of the hydraulic fluid to prevent backflow of the hydraulic fluid.

23. The system of claim 18, further comprising an alternate mode power system coupled to the means for moving the aircraft control surface and dedicated for operation of the means for moving the aircraft control surface.

24. The system of claim 18, further comprising a controller operatively wherein the alternate mode power system includes the flow control member connected to the hydraulic line and operatively coupled to the control computer.