IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
UP-0778995
(2007-07-17)
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등록번호 |
US-7828250
(2010-11-25)
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발명자
/ 주소 |
- Wheaton, James M.
- Amorosi, Stephen R.
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
3 인용 특허 :
208 |
초록
▼
The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links. In a further aspect of
The present invention is directed generally toward leading edge flap apparatuses and corresponding methods. One aspect of the invention is directed toward an aircraft system having an airfoil, an actuator driver, and a leading edge device with two flow surfaces and six links. In a further aspect of the invention, the flow surfaces of the leading edge device are at least approximately located in the same position when the actuator driver is in two different positions. Another aspect of the invention is directed toward an aircraft system having an airfoil and a leading edge device movable between at least a retracted position and an extended position along a motion path having two segments. The second flow surface can be positioned generally behind and/or generally above the first flow surface when the first and second flow surfaces are located in the first segment of the motion path.
대표청구항
▼
We claim: 1. An aircraft system, comprising: an airfoil having a leading edge, a lower surface, and a chord line; and a leading edge device having a first flow surface and a second flow surface, the first flow surface being coupled to the airfoil and the second flow surface being coupled to the fir
We claim: 1. An aircraft system, comprising: an airfoil having a leading edge, a lower surface, and a chord line; and a leading edge device having a first flow surface and a second flow surface, the first flow surface being coupled to the airfoil and the second flow surface being coupled to the first flow surface, the leading edge device being movable along a motion path among: a retracted position; an extended position; and an intermediate position with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has: a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and a second segment between the extended position and the intermediate position along which the second flow surface moves relative to the first flow surface to a fully deployed position. 2. The system of claim 1, further comprising a fuselage coupled to the airfoil and an engine coupled to at least one of the airfoil and the fuselage. 3. The system of claim 1, further comprising an engine having an engine nacelle, the engine nacelle being proximate to the airfoil, and wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine nacelle when the leading edge device is in the extended position. 4. The system of claim 1, further comprising an engine having an engine pylon, the engine pylon being proximate to the airfoil, and wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine pylon when the leading edge device is in the extended position. 5. The system of claim 1, further comprising an engine proximate to the airfoil, the engine having a thrust reverser and an engine nacelle, a portion of the engine nacelle being coupled to the thrust reverser to move when the thrust reverser is deployed, and wherein at least a portion of the leading edge device moves with the portion of the engine nacelle when the leading edge device is moved to the extended position. 6. The system of claim 1 wherein the leading edge device includes a first leading edge device, and wherein the system further comprises a second leading edge device laterally disposed from the first leading edge device, the second leading edge device having an extended position, wherein at least a portion of the first leading edge device is at least approximately aerodynamically sealed against a portion of a lateral edge of the second leading edge device when the first leading edge device is in the extended position and the second leading edge device is in the extended position. 7. The system of claim 1 wherein the second flow surface is discontinuous with the first flow surface while the leading edge device is in the first segment of the motion path. 8. A method of making an aircraft system, comprising: configuring a leading edge device to be couplable to an airfoil, the airfoil having a leading edge, a lower surface, and a chord line, the leading edge device having a first flow surface and a second flow surface; and configuring the leading edge device to be movable along a motion path among: a retracted position; an extended position; and an intermediate portion with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has: a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and a second segment between the extended position and the intermediate position along which the second flow surface moves relative to the first flow surface to a fully deployed position. 9. The method of claim 8, further comprising: providing an aircraft having an airfoil; and coupling the leading edge device to the airfoil. 10. The method of claim 8, further comprising: providing an aircraft having an airfoil and an engine with an engine pylon, the engine pylon being proximate to the airfoil; and coupling the leading edge device to the airfoil wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine pylon when the leading edge device is in the extended position. 11. The method of claim 8, further comprising: providing an aircraft having an airfoil and an engine with an engine nacelle, the engine nacelle being proximate to the airfoil; and coupling the leading edge device to the airfoil wherein at least a portion of the leading edge device is at least approximately aerodynamically sealed against the engine nacelle when the leading edge device is in the extended position. 12. The method of claim 8, further comprising: providing an aircraft with an airfoil and an engine proximate to the airfoil, the engine having an engine nacelle and a thrust reverser, a portion of the engine nacelle being coupled to the thrust reverser to move when the thrust reverser is deployed; and coupling the leading edge device to the airfoil wherein at least a portion of the leading edge device moves with the portion of the engine nacelle that moves with the thrust reverser when the leading edge device is moved to the extended position. 13. The method of claim 8 wherein the leading edge device includes a first leading edge device, and wherein the method further comprises: providing an aircraft with an airfoil, the airfoil having a second leading edge device with a lateral edge and an extended position; and coupling the first leading edge device to the airfoil adjacent to the second leading edge device, wherein at least a portion of the first leading edge device is at least approximately aerodynamically sealed against a portion of the lateral edge of the second leading edge device when the first leading edge device is in the extended position and the second leading edge device is in the extended position. 14. A method for configuring an aircraft for various phases of flight, comprising moving a leading edge device from a stationary retracted position to a stationary extended position, the leading edge device being coupled to an airfoil and having a first and second flow surface, and wherein the second flow surface is positioned at least one of generally behind and generally above the first flow surface while moving from the retracted to the extended position until the first flow surface passes through an intermediate position where the first flow surface is at least approximately perpendicular to a chord line of the airfoil, and wherein the second flow surface moves relative to the first flow surface as the first flow surface moves from the intermediate position to the extended position. 15. The method of claim 14, further comprising operating the aircraft with the leading edge device in at least one of the retracted position and the extended position. 16. An aircraft system, comprising: an airfoil having a leading edge, a lower surface, and a chord line; and leading edge means for forming a retractable extension of the leading edge of the airfoil, the leading edge means having a first flow surface and a second flow surface, the leading edge means coupled to the airfoil and movable along a motion path among: a retracted position; an extended position, and an intermediate position with the first flow surface at least approximately perpendicular to the chord line of the airfoil, and wherein the motion path has: a first segment between the retracted position and the intermediate position along which the second flow surface is positioned at least one of generally behind and generally above the first flow surface; and a second segment between the extended position and the intermediate position along which the second flow surface moves relative to the first flow surface to a fully deployed position. 17. The system of claim 16, further comprising a fuselage coupled to the airfoil and an engine coupled to at least one of the airfoil and the fuselage.
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