초록 ▼

Aircraft and leading edge apparatuses and corresponding methods are disclosed. In one embodiment, an aircraft system includes an airfoil with a leading edge device that is movable among a retracted position, at least one first extended position, and a second extended position. A first actuator can b

Aircraft and leading edge apparatuses and corresponding methods are disclosed. In one embodiment, an aircraft system includes an airfoil with a leading edge device that is movable among a retracted position, at least one first extended position, and a second extended position. A first actuator can be operatively coupled to the leading edge device to move the flow surface between the retracted and the at least one first extended position. A second actuator can be operatively coupled to the leading edge device to move the flow surface between the at least one first extended position and the second extended position.

대표청구항 ▼

We claim: 1. An aircraft system, comprising: an airfoil; a leading edge device having a flow surface, a first link coupled between the airfoil and the flow surface to move the flow surface relative to the air foil, and a second link coupled to the first link, the first link having a pin, the second

We claim: 1. An aircraft system, comprising: an airfoil; a leading edge device having a flow surface, a first link coupled between the airfoil and the flow surface to move the flow surface relative to the air foil, and a second link coupled to the first link, the first link having a pin, the second link having an elongated slot in which the pin is received to pivotally couple the first link to the second link and to permit the second link to translate relative to the first link, the second link being coupled to the flow surface to move the flow surface relative to the first link and relative to the airfoil; a first actuator coupled to the first link to move the first link relative to the airfoil; and a second actuator coupled between the first and second links to move at least one link relative to the other. 2. The system of claim 1, further comprising an aircraft, and wherein the airfoil is coupled to the aircraft. 3. The system of claim 1 wherein the flow surface includes multiple sections movable relative to each other. 4. An aircraft system, comprising: an airfoil having a leading edge and a lower surface; a leading edge device coupled to the airfoil, the leading edge device including a flow surface having a trailing edge, the leading edge device being movable among: a retracted position wherein the flow surface is positioned generally behind the leading edge of the airfoil to form a portion of the lower surface of the airfoil; at least one first extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with a first distance between the trailing edge of the flow surface and the leading edge of the airfoil; and a second extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with no distance or a second distance between the trailing edge of the flow surface and the leading edge of the airfoil, the second distance being smaller than the first distance; a first actuator operatively coupled to the leading edge device to move the leading edge device between the retracted position and the at least one first extended position; and a second actuator operatively coupled to the leading edge device to move the leading edge device between the at least one first extended position and the second extended position. 5. The system of claim 4, further comprising an aircraft, and wherein the airfoil is coupled to the aircraft. 6. The system of claim 4 wherein the leading edge device includes a Krueger flap. 7. The system of claim 4 wherein the first actuator includes a pneumatic actuator. 8. The system of claim 4 wherein the second actuator includes an electric actuator. 9. The system of claim 4 wherein the first and second actuators are configured to operate in a sequential manner. 10. The system of claim 4 wherein the first and second actuators are configured to operate simultaneously to move the leading edge device from the retracted position to the second extended position, to move the leading edge device from the second extended position to the retracted position, or both. 11. The system of claim 4 wherein the flow surface includes multiple sections movable relative to each other. 12. The system of claim 4 wherein: the leading edge device is movable to a third extended position between the first and the second extended positions; and wherein the second actuator is configured to move the leading edge device among the at least one first extended position, the second extended position, and the third extended position. 13. An aircraft system, comprising: an airfoil having a leading edge, a lower surface, and multiple attachment points, the airfoil being configured to be operatively coupled to a first leading edge device at the multiple attachment points, the first leading edge device having a first flow surface and a first number of extended positions; a second leading edge device coupled to the airfoil at the multiple attachment points, the second leading edge device having a second flow surface with a trailing edge and a second number of extended positions, the second number of extended positions being greater than the first number of extended positions, wherein the second leading edge device is movable among: a retracted position wherein the second flow surface is positioned generally behind the leading edge of the airfoil to form a portion of the lower surface of the airfoil; at least one first extended position wherein at least a portion of the second flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with a first distance between the trailing edge of the second flow surface and the leading edge of the airfoil; and a second extended position wherein at least a portion of the second flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with no distance or a second distance between the trailing edge of the second flow surface and the leading edge of the airfoil, the second distance smaller than the first distance; and wherein the system further comprises: a first actuator operatively coupled to the second leading edge device to move the second leading edge device surface between the retracted position and the at least one first extended position; and a second actuator operatively coupled to the second leading edge device to move the second leading edge device between the at least one first extended position and the second extended position. 14. The system of claim 13, further comprising an aircraft, and wherein the airfoil is coupled to the aircraft. 15. The system of claim 13 wherein the second leading edge device includes at least one of a link, a pin, and at least a portion of a flow surface that is at least approximately identical to a corresponding link, pin, and flow surface portion of the first leading edge device. 16. The system of claim 13 wherein the first actuator is configured to be operatively couplable to the first leading edge device to move the first flow surface. 17. The system of claim 13 wherein: the first flow surface of the first leading edge device is at least approximately identical to the second flow surface of the second leading edge device; and wherein the first leading edge device, when operatively coupled to the airfoil, is movable between: a first position that places the first flow surface in a position relative to the airfoil that is at least approximately identical to the position of the second flow surface when the second leading edge device is in the first extended position; and a second position that places the first flow surface in a position relative to the airfoil that is at least approximately identical to the position of the second flow surface when the second leading edge device is in the retracted position. 18. An aircraft system, comprising: an airfoil having a leading edge and a lower surface; a leading edge device coupled to the airfoil, the leading edge device including: a flow surface having a trailing edge; a drive arm, the drive arm being coupled to the flow surface and configured to rotate the flow surface generally forward and downward from the retracted position, the drive arm having a pin; a scissors link, the scissors link having a slot in which the pin is received to pivotally couple the drive arm and the scissors link and to permit the scissors link to translate relative to the drive arm, the scissors link being coupled to the flow surface to move the flow surface relative to the drive arm; and wherein the leading edge device is movable among: a retracted position wherein the flow surface is positioned generally behind the leading edge of the airfoil to form a portion of the lower surface of the airfoil; at least one first extended position wherein at least a portion of the flow surface is positioned to form an extension of the leading edge with a first distance between the trailing edge of the flow surface and the leading edge of the airfoil; and a second extended position wherein at least a portion of the flow surface is positioned to form an extension of the leading edge with no distance or a second distance between the trailing edge of the flow surface and the leading edge of the airfoil, the second distance being smaller than the first distance; a first actuator operatively coupled to the drive arm to move the leading edge device between the retracted position and the at least one first extended position; and a second actuator operatively coupled to the scissors link and the drive arm to translate the scissors link and move the leading edge device between the at least one first extended position and the second extended position. 19. The system of claim 18 wherein the scissors link is coupled to the flow surface to change at least one of a position and an orientation of the flow surface relative to the drive arm. 20. The system of claim 18, further comprising an aircraft, and wherein the airfoil is coupled to the aircraft. 21. The system of claim 18 wherein the first actuator is coupled to the airfoil and the leading edge device. 22. The system of claim 18 wherein the first and second actuators are configured to operate in a sequential manner. 23. The system of claim 18 wherein the first and second actuators are configured to operate simultaneously to move the leading edge device from the retracted position to the second extended position, to move the second flow surface from the second extended position to the retracted position, or both. 24. An aircraft system, comprising: an airfoil having a leading edge and a lower surface; leading edge extension means for extending the leading edge, the leading edge extension means having a flow surface with a trailing edge, the leading edge extension means being movable among: a retracted position wherein the flow surface is positioned generally behind the leading edge of the airfoil to form a portion of the lower surface of the airfoil; at least one first extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with a first distance between the trailing edge of the flow surface and the leading edge of the airfoil; and a second extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with no distance or a second distance between the trailing edge of the flow surface and the leading edge of the airfoil, the second distance being smaller than the first distance; first actuator means for moving the leading edge extension means between the retracted position and the at least one first extended position; and second actuator means for moving the leading edge extension means between the at least one first extended position and the second extended position. 25. The system of claim 24, further comprising an aircraft, and wherein the airfoil is coupled to the aircraft. 26. The system of claim 24 wherein the first actuator means is coupled to the airfoil and the leading edge device means. 27. The system of claim 24 wherein: the leading edge extension means is movable to a third extended position between the first and second extended positions; and wherein the second actuator means is configured to move the leading edge extension means among the at least one first extended position, the second extended position, and the third extended position. 28. A method for making an aircraft system, comprising: providing an airfoil; installing a leading edge device having a flow surface on the airfoil, the leading edge device having a first link coupled between the airfoil and the flow surface to move the flow surface relative to the air foil and a second link coupled to the first link, the first link having a pin, the second link having an elongated slot in which the pin is received to pivotally couple the first link to the second link and to permit the second link to translate relative to the first link, the second link being coupled to the flow surface to move the flow surface relative to the first link and relative to the airfoil; operatively coupling a first actuator to the first link to move the first link relative to the airfoil; and operatively coupling a second actuator between the first and second links to move at least one link relative to the other. 29. The method of claim 28, further comprising installing the airfoil on an aircraft. 30. The method of claim 28 wherein installing a leading edge device includes installing a leading edge device having a flow surface with multiple sections movable relative to each other. 31. A method for making an aircraft system, comprising: providing an airfoil having a leading edge and a lower surface; installing the leading edge device on the airfoil, the leading edge device including a flow surface and a trailing edge, the leading edge device being movable among: a retracted position wherein the flow surface is positioned generally behind the leading edge of the airfoil to form a portion of the lower surface of the airfoil; at least one first extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with a first distance between the trailing edge of the flow surface and the leading edge of the airfoil; and a second extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with no distance or a second distance between the trailing edge of the flow surface and the leading edge of the airfoil, the second distance being smaller than the first distance; operatively coupling a first actuator to the leading edge device to move the leading edge device between the retracted position and the at least one first extended position; and operatively coupling a second actuator to the leading edge device to move the leading edge device between the at least one first extended position and the second extended position. 32. The method of claim 31, further comprising installing the airfoil on an aircraft. 33. The method of claim 31, further comprising moving the flow surface to at least one of the retracted position, the at least one first extended position, and the second extended position. 34. The method of claim 31 wherein installing a leading edge device includes installing a leading edge device that includes a Krueger flap. 35. The method of claim 31, further comprising coupling the first actuator to the airfoil. 36. The method of claim 31 wherein installing a leading edge device includes installing a leading edge device having a flow surface with multiple sections that are movable relative to each other. 37. The method of claim 31 wherein: installing a leading edge device includes installing a leading edge device that is movable to a third extended position between the first extended position and the second extended position; and wherein operatively coupling a second actuator to the leading edge device includes operatively coupling a second actuator to the leading edge device to move the flow surface among the at least one first extended position, the second extended position, and the third extended position. 38. The method of claim 31 wherein installing the leading edge device on the airfoil includes installing a leading edge device by: connecting a drive arm to the flow surface to rotate the flow surface generally forward and down from the retracted position; coupling a pin of the drive arm with a slot of the scissors link to pivotally couple the drive arm and the scissors link and to permit the scissors link to translate relative to the drive arm; and connecting the scissors link to the flow surface to move the flow surface relative to the drive arm; and wherein operatively coupling a second actuator to the leading edge device includes operatively coupling a second actuator to the scissors link and the drive arm to translate the scissors link and move the leading edge device between the at least one first extended position and the second extended position. 39. A method for making an aircraft system, comprising: providing an airfoil having a leading edge, a lower surface, and multiple attachment points, the airfoil being operatively couplable to a first leading edge device at the multiple attachment points, the first leading edge device having a first number of extended positions; and operatively coupling a second leading edge device to the airfoil via the attachment points, the second leading edge device having a second number of extended positions, the second number of extended positions being greater than the first number of extended positions, wherein the second leading edge device is movable among: a retracted position wherein a flow surface of the second leading edge device is positioned generally behind the leading edge of the airfoil to form a portion of the lower surface of the airfoil; at least one first extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with a first distance between a trailing edge of the flow surface and the leading edge of the airfoil; and a second extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with no distance or a second distance between the trailing edge of the flow surface and the leading edge of the airfoil, the second distance being smaller than the first distance; and wherein the method further comprises: operatively coupling a first actuator to the second leading edge device to move the second leading edge device surface between the retracted position and the at least one first extended position; and operatively coupling a second actuator to the second leading edge device to move the second leading edge device between the at least one first extended position and the second extended position. 40. The method of claim 39 wherein providing an airfoil includes providing an airfoil operatively coupled to the first leading edge device and wherein the method further comprises removing the first leading edge device from the airfoil before operatively coupling the second leading edge device. 41. The method of claim 39 wherein providing an airfoil includes providing an airfoil coupled to the first actuator, the first actuator being coupled to the first leading edge device, and wherein the method further comprises decoupling the first leading edge device from the first actuator and removing the first leading edge device from the airfoil. 42. The method of claim 39 wherein providing an airfoil includes providing an airfoil attached to an aircraft. 43. The method of claim 39 wherein installing a second leading edge device includes installing a second leading edge device that includes at least one of a link, a pin, and at least a portion of a flow surface that is at least approximately identical to a corresponding link, pin, and portion of a flow surface of the first leading edge device. 44. The method of claim 39 wherein the flow surface of the second leading edge device includes a second flow surface, and wherein providing an airfoil includes providing an airfoil operatively coupled to the first leading edge device, the first leading edge device including a first flow surface, and further wherein operatively coupling a second leading edge device to the airfoil includes operatively coupling a second leading edge device to the airfoil wherein the second flow surface is at least approximately identical to the first flow surface of the first leading edge device. 45. A method for configuring an aircraft for various phases of flight, comprising: activating a first actuator to move a leading edge device from a retracted position wherein a flow surface of the device forms a portion of a lower surface of an airfoil to at least one first extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of a leading edge of the airfoil with a first distance between a trailing edge of the flow surface and the leading edge of the airfoil; and activating a second actuator to move the leading edge device to a second extended position wherein at least a portion of the flow surface is positioned forward of the leading edge of the airfoil to form an extension of the leading edge with no distance or a second distance between the trailing edge of the flow surface and the leading edge of the airfoil, the second distance being smaller than the first distance. 46. The method of claim 45, further comprising operating the aircraft in a takeoff phase of flight with the leading edge device in the second extended position. 47. The method of claim 45, further comprising: positioning the leading edge device in the retracted position; and operating the aircraft in cruise with the leading edge device in the retracted position. 48. The method of claim 45, further comprising operating the aircraft in a landing phase of flight with the leading edge device in the first extended position.