Aircraft control surface controller and associated method

• US 20030183728A1
• Filed: 03/29/2002
• Published: 10/02/2003
• Est. Priority Date: 03/29/2002
• Status: Abandoned Application

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Huynh, Neal V.
• Application Number:
  US10/112,815
• Publication Number:
  US 20030183728A1
• Time in Patent Office: Days
• US Class Current: 244/224
• CPC Class Codes: B64C 13/345 with artificial feel

Abstract

A control surface controller and a method of controlling a control surface interface includes a control surface interface for controlling one or more of the aerodynamic control surfaces on an aircraft, such as ailerons, spoilers, elevators, and a rudder. A control surface controller and a method of controlling a control surface interface also include a variable resistance damper that provides physical resistance to the control surface interface in proportion to control surface interface input rate. Accordingly, the resistance provided to the control surface interface may be selected in order to prevent the cause of pilot-induced-oscillation or airplane-pilot coupling. The resistance provided to the control surface interface may also be selected in order to limit the servovalve rate which reduces peak transient hydraulic fluid pressure in the hydraulic system.

Claims

1. An aircraft control surface controller for controlling aerodynamic control surfaces on an aircraft, comprising:

a control surface interface having a range of motion for providing pilot input for positioning the aerodynamic control surfaces on an aircraft; and

a variable resistance damper mechanically interconnected to the pilot control surface interface, wherein the damper provides physical resistance to the control surface interface, the damper physical resistance increases proportional to a rate of movement of the control surface interface.

2. The aircraft control surface controller according to claim 1, wherein the variable resistance damper provides physical resistance to the control surface interface once the control surface interface exceeds an initial damping criterion corresponding to a predetermined rate of the control surface interface.

3. The aircraft control surface controller according to claim 2, wherein the variable resistance damper provides physical resistance to the control surface interface according to a second initial damping criterion corresponding to a predetermined position of the control surface interface from a nominal position of the control surface interface.

4. The aircraft control surface controller according to claim 2, wherein the variable resistance damper initial damping criterion and physical resistance are selected based upon the physical response properties and aerodynamic effect properties of the control surfaces in response to the control surface interface.

5. The aircraft control surface controller according to claim 1, further comprising an aerodynamic control surface responsive to the control surface interface.

6. The aircraft control surface controller according to claim 5, further comprising mechanical linkages interconnecting the control surface interface and the control surface.

7. The aircraft control surface controller according to claim 5, further comprising electromechanical devices interconnecting the control surface interface and the control surface.

8. The aircraft control surface controller according to claim 5, wherein the control surface is selected from the group consisting of an aileron, spoiler, rudder, flap, and elevator.

9. The aircraft control surface controller according to claim 1, wherein the variable resistance damper comprises an electromagnetic damper.

10. The aircraft control surface controller according to claim 9, wherein the electromagnetic damper comprises an eddy current drag device.

11. The aircraft control surface controller according to claim 9, wherein the electromagnetic damper comprises an electric motor.

12. The aircraft control surface controller according to claim 11, wherein the proportional resistance is established by electrically controlling a torque of the motor.

13. The aircraft control surface controller according to claim 11, wherein the electromagnetic damper further comprises a generator.

14. The aircraft control surface controller according to claim 1, wherein the variable resistance damper comprises a mechanical brake.

15. The aircraft control surface controller according to claim 14, wherein the mechanical brake comprises a centrifugal friction braking mechanism.

16. The aircraft control surface controller according to claim 1, further comprising a mechanical gear train interconnecting the control surface interface and the variable resistance damper.

17. The aircraft control surface controller according to claim 16, further comprising a clutch interconnecting the control surface interface and the variable resistance damper.

18. The aircraft control surface controller according to claim 16, further comprising a rivet assembly capable of being sheared at a predetermined force, the rivet interconnecting the control surface interface and the variable resistance damper.

19. The aircraft control surface controller according to claim 1, wherein the variable resistance damper is self contained.

20. An aircraft control surface controller, comprising:

a control surface interface having a range of motion for providing pilot input;

at least two aerodynamic control surfaces responsive to the control surface interface based on the pilot input; and

a variable resistance damper mechanically interconnected to the control surface interface, wherein the damper provides physical resistance to the control surface interface, the damper physical resistance increases proportional to a rate of movement of the control surface interface.

21. The aircraft control surface controller according to claim 20, further comprising a jam override device interconnecting one of the at least two control surfaces and the control surface interface, wherein the jam override device permits operation of one of the at least two control surfaces while the one control surface is in a jammed condition.

22. The aircraft control surface controller according to claim 21, wherein the jam override device has a preset detent force.

23. The aircraft control surface controller according to claim 20, wherein the variable resistance damper provides physical resistance to the control surface interface once the control surface interface exceeds an initial damping criterion corresponding to a predetermined rate of the control surface interface.

24. The aircraft control surface controller according to claim 23, wherein the variable resistance damper provides physical resistance to the control surface interface once the control surface interface exceeds a second initial damping criterion corresponding to a predetermined position of the control surface interface from a nominal position of the control surface interface.

25. The aircraft control surface controller according to claim 23, wherein the variable resistance damper initial damping criterion and physical resistance are selected based upon the physical response properties and aerodynamic effect properties of the control surfaces in response to the control surface interface.

26. The aircraft control surface controller according to claim 20, wherein the control surface is selected from the group consisting of an aileron, spoiler, rudder, and elevator.

27. The aircraft control surface controller according to claim 20, wherein the variable resistance damper comprises an electromagnetic damper.

28. The aircraft control surface controller according to claim 27, wherein the electromagnetic damper comprises an eddy current drag device.

29. The aircraft control surface controller according to claim 27, wherein the electromagnetic damper comprises an electric motor.

30. The aircraft control surface controller according to claim 29, wherein the proportional resistance is established by electrically controlling a torque of the motor.

31. The aircraft control surface controller according to claim 29, wherein the electromagnetic damper further comprises a generator.

32. The aircraft control surface controller according to claim 20, wherein the variable resistance damper comprises a mechanical brake.

33. The aircraft control surface controller according to claim 32, wherein the mechanical brake comprises a centrifugal friction braking mechanism.

34. The aircraft control surface controller according to claim 20, further comprising a mechanical gear train interconnecting the control surface interface and the variable resistance damper.

35. The aircraft control surface controller according to claim 34, further comprising a clutch interconnecting the control surface interface and the variable resistance damper.

36. The aircraft control surface controller according to claim 34, further comprising a rivet assembly capable of being sheared at a predetermined force, the rivet interconnecting the control surface interface and the variable resistance damper.

37. The aircraft control surface controller according to claim 20, further comprising mechanical linkages interconnecting the control surface interface and the control surface.

38. The aircraft control surface controller according to claim 20, further comprising electromechanical devices interconnecting the control surface interface and the control surface.

39. The aircraft control surface controller according to claim 20, wherein the variable resistance damper is self contained.

40. A method of controlling a control surface interface that controls an aerodynamic control surface on an aircraft, comprising:

receiving an input rate from the control surface interface; and

applying an increasing physical resistance to the control surface interface proportional to the input rate.

41. The method according to claim 40, wherein applying the physical resistance occurs once the control surface interface has moved beyond an initial damping criteria, wherein at least one initial damping criteria corresponds to a predetermined input rate of the control surface interface.

42. The method according to claim 41, wherein applying the physical resistance occurs beyond initial damping criteria, and at least one initial damping criteria corresponds to a predetermined position of the control surface interface from a nominal position of the control surface interface.

43. The method according to claim 41, wherein the step of applying the physical resistance includes initial damping criteria that are selected based upon the physical response properties and aerodynamic effect properties of at least one aerodynamic control surface in response to the control surface interface.