Systems and methods for providing differential motion to wing high lift devices

• US 20060049308A1
• Filed: 09/08/2004
• Published: 03/09/2006
• Est. Priority Date: 09/08/2004
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Good, Mark S., Viigen, Paul M., Thomas, Glynn Michael, Gitnes, Seth E.
• Granted Patent: US 7,494,094 B2
• Time in Patent Office: Days
• US Class Current: 244/76.A
• CPC Class Codes: B64C 13/26 without power amplification or where power amplification is irrelevant
• CPC Class Codes: B64C 3/50 by leading or trailing edge flaps
• CPC Class Codes: B64C 9/14 forming slots
• CPC Class Codes: Y02T 50/10 Drag reduction
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable lift device with a second spanwise location different than the first. The wing system can further include a drive system having a drive link operatively coupleable to both the first and second deployable lift devices, and a control system operatively coupled to the drive system. The control system can have a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together. In a second configuration, the drive link is operatively coupled to at least the first deployable lift device and operatively decoupled from the second deployable lift device, so that actuation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device.

Claims

1. An aircraft wing system, comprising:

a wing having a leading edge and a trailing edge;

a first deployable lift device having a first spanwise location and being movable relative to the wing from a stowed position to at least one first deployed position;

a second deployable lift device having a second spanwise location different than the first and being movable relative to the wing from a stowed position to at least one second deployed position;

a drive system having an drive link operatively coupleable to both the first and the second deployable lift devices; and

a control system operatively coupled to the drive system, the control system having;

a first configuration for which for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together; and

a second configuration for which the drive link is operatively coupled to the first deployable lift device and operatively decoupled from the second deployable lift device, and activation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device.

2. The system of claim 1 wherein the control system has a third configuration for which the drive link is operatively coupled to the second deployable lift device and operatively decoupled from the first deployable lift device, and wherein activation of at least a portion of the drive link moves the second deployable lift device relative to the first deployable lift device.

3. The system of claim 1, further comprising a range limiter operatively coupled to the first and second deployable lift devices to provide a first range of motion when the control system has the first configuration, and provide a second range of motion less than the first range of motion when the control system has the second configuration.

4. The system of claim 1 wherein the drive link includes a mechanical drive shaft.

5. The system of claim 1 wherein the first deployable lift device is inboard of the second deployable lift device.

6. The system of claim 1 wherein the first deployable lift device is outboard of the second deployable lift device.

7. The system of claim 1 wherein the drive link includes a hydraulic link.

8. The system of claim 1 wherein the control system has a third configuration for which the drive link is operatively coupled to the second deployable lift device and operatively decoupled from the first deployable lift device, and wherein activation of at least a portion of the drive link moves the second deployable lift device relative to the first deployable lift device, and wherein the drive link includes a drive shaft and the drive system includes a first motor and a second motor, and wherein the control system includes:

a differential coupled among the drive shaft, the first deployable lift device, the second deployable lift device and the second motor;

a first brake operatively coupled to the differential and engaged to move the first and second deployable lift devices when the control system has the first configuration;

a second brake operatively coupled to the second deployable lift device and engaged to at least resist motion of the second deployable lift device when the control system has the second configuration; and

a third brake operatively coupled to the first deployable lift device and engaged to at least resist motion of the first deployable lift device when the control system has the third configuration;

wherein

the first motor is operatively coupled to the first and second deployable lift devices and the second motor is operatively decoupled from the first and second deployable lift devices when the control system has the first configuration;

the second motor is operatively coupled to the first deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the second configuration; and

the second motor is operatively coupled to the second deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the third configuration.

9. The system of claim 1 wherein the drive link includes a drive shaft and the drive system includes a motor coupled to the drive shaft, and wherein the control system includes:

a differential coupled among the drive shaft, the first deployable lift device, and the second deployable lift device;

a first brake operatively coupled to the differential to couple the first and second deployable lift devices when the control system has the first configuration; and

a second brake operatively coupled to the second deployable lift device and engaged to resist motion of the second deployable lift device when the control system has the second configuration.

10. The system at claim 1, further comprising a fuselage coupled to the wing.

11. An aircraft wing system, comprising:

a wing having a leading edge and a trailing edge;

a first deployable lift device positioned proximate to the wing leading edge or the wing trailing edge at a first spanwise location, the first deployable lift device being movable relative to the wing from a stowed position to at least one first deployed position;

a second deployable lift device positioned proximate to the wing leading edge or the wing trailing edge at a second spanwise location different than the first, the second deployable lift device being movable relative to the wing from a stowed position to at least one second deployed position;

a drive system having a drive link operatively coupleable to both the first and the second deployable lift devices; and

a control system operatively coupled to the drive link, the control system having;

a first configuration for which activation of at least a portion of the drive link moves the first and second deployable lift devices together;

a second configuration for which activation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device; and

a third configuration for which activation of at least a portion of the drive link moves the second deployable lift device relative to the first deployable lift device.

12. The system of claim 11 wherein the drive link includes a drive shaft and wherein the drive system includes a first motor and a second motor, and wherein the control system includes:

a differential coupled among the drive shaft, the first deployable lift device, the second deployable lift device and the second motor;

a first brake operatively coupled to the differential and engaged to move the first and second deployable lift devices when the control system has the first configuration;

a second brake operatively coupled to the second deployable lift device and engaged to at least resist motion of the second second deployable lift device when the control system has the second configuration; and

a third brake operatively coupled to the first deployable lift device and engaged to at least resist motion of the first deployable lift device when the control system has the third configuration;

wherein

the first motor is operatively coupled to the first and second deployable lift devices and the second motor is operatively decoupled from the first and second deployable lift devices when the control system has the first configuration;

the second motor is operatively coupled to the first deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the second configuration; and

the second motor is operatively coupled to the second deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control system has the third configuration.

13. The system of claim 11 wherein the drive link includes a mechanical drive shaft.

14. The system of claim 11 wherein the first deployable lift device is inboard of the second deployable lift device.

15. The system of claim 11 wherein the first deployable lift device is outboard of the second deployable lift device.

16. The system of claim 11 wherein the drive link includes a hydraulic link.

17. An aircraft wing system, comprising:

a wing having a leading edge and a trailing edge;

a first deployable lift device positioned proximate to the wing trailing edge at a first spanwise location, the first deployable lift device being movable relative to the wing from a stowed position to at least one first deployed position;

a second deployable lift device positioned proximate to the wing trailing edge at a second spanwise location different than the first, the second deployable lift device being movable relative to the wing from a stowed position to at least one second deployed position;

a drive system having a drive link operatively coupleable to both the first and the second deployable lift devices; and

a control system operatively coupled to the drive system, the control system having;

a first configuration for which activation of at least a portion of the drive link moves the first and second deployable lift devices together;

a second configuration for which activation of at least a portion of the drive link moves the first deployable lift device relative to the second deployable lift device;

a differential coupled among the drive link, the first deployable lift device, and the second deployable lift device;

a first brake operatively coupled to the differential to couple the first and second deployable lift devices when the control system has the first configuration; and

a second brake operatively coupled to the second deployable lift device and engaged to at least restrict motion of the second deployable lift device when the control system has the second configuration.

18. The system of claim 17, further comprising:

a first motor coupled to the drive link when the control system has the first configuration and decoupled from the drive link when the control system has the second configuration; and

a second motor coupled to the drive link when the control system has the second configuration and decoupled from the drive link when the control system has the first configuration.

19. The system of claim 17 wherein the first deployable lift device is inboard of the second deployable lift device.

20. The system of claim 17 wherein the first deployable lift device is outboard of the second deployable lift device.

21. An aircraft wing system, comprising:

a wing having a leading edge and a trailing edge;

a first deployable lift device having a first spanwise location, the first deployable lift device being movable relative to the wing from a stowed position to at least one first deployed position;

a second deployable lift device having a second spanwise location different than the first, the second deployable lift device being movable relative to the wing from a stowed position to at least one second deployed position;

drive means having link means operatively coupleable to both the first and the second deployable lift devices; and

control means operatively coupled to the drive means, the control means having;

a first configuration for which the link means is operatively coupled to the first deployable lift device and activation of at least a portion of the link means moves the first and second deployable lift devices as a unit; and

a second configuration for which the link means is operatively coupled to the first deployable lift device and operatively decoupled from the second deployable lift device, and activation of at least a portion of the link means moves the first deployable lift device relative to the second deployable lift device.

22. The system of claim 21 wherein the control means has a third configuration for which the link means is operatively coupled to the second deployable lift device and operatively decoupled from the first deployable lift device, and wherein activation of at least a portion of the link means moves the second deployable lift device relative to the first deployable lift device.

23. The system of claim 21 wherein the first and second deployable lift devices have a first range of motion when the control means has the first configuration, and wherein the first deployable lift device has a second range of motion less than the first range of motion when the control means has the second configuration.

24. The system of claim 21 wherein the link means includes a mechanical drive shaft.

25. The system of claim 21 wherein the first deployable lift device is inboard of the second deployable lift device.

26. The system of claim 21 wherein the first deployable lift device is outboard of the second deployable lift device.

27. The system of claim 21 wherein the link means includes a hydraulic link.

28. The system of claim 21 wherein the control means has a third configuration for which the link means is operatively coupled to the second deployable lift device and operatively decoupled from the first deployable lift device, and wherein activation of at least a portion of the link means moves the second deployable lift device relative to the first deployable lift device, and wherein the link means includes a drive shaft and the drive means includes a first motor and a second motor, and wherein the control means includes:

a differential coupled among the drive shaft, the first deployable lift device, the second deployable lift device and the second motor;

a first brake operatively coupled to the differential and engaged to move the first and second deployable lift devices when the control means has the first configuration;

a second brake operatively coupled to the second deployable lift device and engaged to at least resist motion of the second deployable lift device when the control means has the second configuration; and

a third brake operatively coupled to the first deployable lift device and engaged to at least resist motion of the first deployable lift device when the control means has the third configuration;

wherein

the first motor is operatively coupled to the first and second deployable lift devices and the second motor is operatively decoupled from the first and second deployable lift devices when the control means has the first configuration;

the second motor is operatively coupled to the first deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control means has the second configuration; and

the second motor is operatively coupled to the second deployable lift device and the first motor is operatively decoupled from the first and second deployable lift devices when the control means has the third configuration.

29. The system of claim 21 wherein the link means includes a drive shaft and the drive means includes a motor coupled to the drive shaft, and wherein the control means includes:

a differential coupled among the drive shaft, the first deployable lift device, and the second deployable lift device;

a first brake operatively coupled to the differential to couple the first and second deployable lift devices when the control means has the first configuration; and

a second brake operatively coupled to the second deployable lift device and engaged to resist motion of the first deployable lift device when the control means has the second configuration.

30. A method for operating an aircraft wing system, comprising:

coupling first and second deployable lift devices of a wing with a drive link, the first and second deployable lift devices being located at different spanwise locations of the wing;

moving the first and second deployable lift devices together by activating the drive link;

decoupling the second deployable lift device from the drive link; and

moving the first deployable lift device relative to the second deployable lift device by activating the drive link while the second deployable lift device is decoupled from the drive link.

31. The method of claim 30 wherein moving the first deployable lift device relative to the second deployable lift device includes moving the first deployable lift device in a different direction than the second deployable lift device.

32. The method of claim 30 wherein moving the first deployable lift device relative to the second deployable lift device includes moving the first deployable lift device at a different rate than the second deployable lift device.

33. The method of claim 30 wherein moving the first deployable lift device relative to the second deployable lift device includes moving the first deployable lift device while the second deployable lift device is at least approximately fixed relative to the wing.

34. The method of claim 30, further comprising:

coupling the second deployable lift device to the drive link;

decoupling the first deployable lift device from the drive link; and

moving the second deployable lift device relative to the first deployable lift device by activating the drive link while the first deployable lift device is decoupled from the drive link.

35. The method of claim 30, further comprising limiting a range of motion of the first deployable lift device to have first value when moving the first and second deployable lift devices together, and limiting the range of motion of the first deployable lift device to have a second value less than the first value when moving the first deployable lift device relative to the second deployable lift device.

36. The method of claim 30 wherein activating the drive link includes activating a mechanical drive shaft.

37. The method of claim 30 wherein moving the first deployable lift device includes moving a first deployable lift device that is inboard of the second deployable lift device.

38. The method of claim 30 wherein moving the first deployable lift device includes moving a first deployable lift device that is outboard of the second deployable lift device.

39. The method of claim 30 wherein activating the drive link includes activating a hydraulic link.

40. The method of claim 30 wherein moving the first deployable lift device relative to the second deployable lift device includes providing the wing with a first camber at a section of the wing aligned with the first deployable lift device, and providing the wing with a second camber different than the first camber at a section of the wing aligned with the second deployable lift device

41. The method of claim 30 wherein moving the first and second deployable lift devices together includes moving the first and second deployable lift devices with a first motor, and wherein moving the first deployable lift device relative to the second deployable lift device includes moving the first deployable lift device with a second motor different than the first motor.

42. The method of claim 30 wherein moving the first and second deployable lift devices together includes moving the first and second deployable lift devices while a differential that is operatively coupled to the first and second deployable lift devices has a first setting, and wherein moving the first deployable lift device relative to the second deployable lift device includes moving the first deployable lift device while the differential has a second setting different than the first setting.

43. A method for operating an aircraft wing system, comprising:

coupling first and second deployable lift devices of wing to a rotatable drive shaft, the first and second deployable lift devices being located at different spanwise locations of the wing;

moving the first and second deployable lift devices together during low speed aircraft operations by rotating the drive shaft while both the first and second deployable lift devices are coupled to the drive shaft;

controlling a spanwise camber distribution of the wing during high speed aircraft operations by;

decoupling the second deployable lift device from the drive shaft; and

moving the first deployable lift device independently of the second deployable lift device by rotating the drive shaft while the second deployable lift device is decoupled from the drive shaft.

44. The method of claim 43 wherein controlling a spanwise camber distribution further includes:

decoupling the first deployable lift device from the drive shaft and coupling the second deployable lift device with the drive shaft; and

moving the second deployable lift device independently of the first deployable lift device by rotating the drive shaft while the first deployable lift device is decoupled from the drive shaft.

45. The method of claim 43 wherein moving the first deployable lift device independently of the second deployable lift device includes moving the first deployable lift device in a different direction than the second deployable lift device.

46. The method of claim 43 wherein moving the first deployable lift device independently of the second deployable lift device includes moving the first deployable lift device at a different rate than the second deployable lift device.

47. The method of claim 43 wherein moving the first deployable lift device independently of the second deployable lift device includes moving the first deployable lift device while the second deployable lift device is at least approximately fixed relative to the wing.

48. The method of claim 43, further comprising limiting a range of motion of the first deployable lift device to have first value when moving the first and second deployable lift devices together, and limiting the range of motion of the first deployable lift device to have a second value less than the first value when moving the first deployable lift device independently of the second deployable lift device.

49. The method of claim 43 wherein moving the first deployable lift device includes moving a first deployable lift device that is inboard of the second deployable lift device.

50. The method of claim 43 wherein moving the first deployable lift device includes moving a first deployable lift device that is outboard of the second deployable lift device.

51. The method of claim 43 wherein moving the first and second deployable lift devices together includes moving the first and second deployable lift devices with a first motor, and wherein moving the first deployable lift device independently of the second deployable lift device includes moving the first deployable lift device with a second motor different than the first motor.

52. The method of claim 43 wherein moving the first and second deployable lift devices together includes moving the first and second deployable lift devices while a differential that is operatively coupled to the first and second deployable lift devices has a first setting, and wherein moving the first deployable lift device independently of the second deployable lift device includes moving the first deployable lift device while the differential has a second setting different than the first setting.

53. A method for outfitting an aircraft wing system, comprising

coupling a differential in a drive link between a first deployable lift device of an aircraft and a second deployable lift device of the aircraft;

and

coupling a control system to the differential, wherein the control system has a first configuration for which activation of the drive link moves the first and second deployable high lift devices together, and a second configuration for which activation of the drive link moves the first deployable lift device relative to the second deployable lift device.

54. The method of claim 53, further comprising coupling a range limiter to the differential to control a range of motion of the first deployable lift device to have a first value when the control system has the first configuration, and a second value less than the first value when the control system has the second configuration.

55. An aircraft system that includes a computer-readable medium configured to perform a method that includes:

directing the coupling of first and second deployable lift devices with a drive link, the first and second deployable lift devices being located at different spanwise locations of the wing;

directing the first and second deployable lift devices to move together by activating the drive link;

directing the decoupling of the second deployable lift device from the drive link; and

directing the first deployable lift device to move relative to deployable lift device by activating the drive link while the second deployable lift device is decoupled from the drive link.

56. The system of claim 55 wherein directing the first deployable lift device to move relative to the second deployable lift device includes directing the first deployable lift device to move in a different direction than the second deployable lift device.

57. The system of claim 55 wherein directing the first deployable lift device to move relative to the second deployable lift device includes directing the first deployable lift device to move at a different rate than the second deployable lift device.

58. The system of claim 55 wherein directing the first deployable lift device to move relative to the second deployable lift device includes directing the first deployable lift device to move while the second deployable lift device is at least approximately fixed relative to the wing.

59. The system of claim 55, further comprising:

directing the coupling of the second deployable lift device to the drive link;

directing the decoupling the first deployable lift device from the drive link; and

directing the second deployable lift device to move relative to the first deployable lift device by activating the drive link while the first deployable lift device is decoupled from the drive link.

60. The system of claim 55, further comprising limiting a range of motion of the first deployable lift device to have first value when moving the first and second deployable lift devices together, and limiting the range of motion of the first deployable lift device to have a second value less than the first value when moving the first deployable lift device relative to the second deployable lift device.

61. The system of claim 55 wherein activating the drive link includes activating a mechanical drive shaft.

62. The system of claim 55 wherein directing the first deployable lift device to move includes directing a first deployable lift device that is inboard of the second deployable lift device.

63. The system of claim 55 wherein directing the first deployable lift device to move includes directing a first deployable lift device that is outboard of the second deployable lift device.

64. The system of claim 55 wherein activating the drive link includes activating a hydraulic link.

65. The system of claim 55 wherein directing the first deployable lift device to move relative to the second deployable lift device includes providing the wing with a first camber at a section of the wing aligned with the first deployable lift device, and providing the wing with a second camber different than the first camber at a section of the wing aligned with the second deployable lift device

66. The system of claim 55 wherein directing the first and second deployable lift devices to move together includes directing a first motor to move the first and second deployable lift devices, and wherein directing the first deployable lift device to move relative to the second deployable lift device includes directing a second motor different than the first motor to move the first deployable lift device.

67. The system of claim 55 wherein directing the first and second deployable lift devices to move together includes directing the first and second deployable lift devices to move while being coupled a differential that has a first setting, and wherein directing the first deployable lift device relative to the second deployable lift device includes directing the first deployable lift device to move while the differential has a second setting different than the first setting.