IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0326016
(2006-01-05)
|
등록번호 |
US-7568657
(2009-08-24)
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발명자
/ 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
3 |
초록
▼
A vertical take-off and landing (VTOL) aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rud
A vertical take-off and landing (VTOL) aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage with movable surfaces for controlling the aircraft; and (3) a wing on each side of the fuselage having a front edge, a trailing edge and an upper surface extending from the front edge to the trailing edge. According to the invention, means are provided for increasing the speed of an airstream flowing over the upper surface of each wing, and an air deflector is disposed on each side of the fuselage between the trailing edge of each wing and the aircraft tail. These deflectors each have a deflection surface to deflect downward the airstream flowing over the upper surface of the wing to act as a "brake" to the forward motion of the aircraft and to provide additional lift so that the aircraft may hover.
대표청구항
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What is claimed is: 1. A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the r
What is claimed is: 1. A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft; (c) a wing on each side of the fuselage, each wing having a front edge, a rear edge and an upper surface extending from the front edge to the rear edge thereof; (d) means for increasing the speed of an airstream flowing over the upper surface of each wing; and (e) an air deflector disposed on each side of the fuselage between the rear edge of each wing and the aircraft tail and having a deflection surface to deflect the airstream flowing over the upper surface of the wing in both a downward and a forward direction. 2. The aircraft defined in claim 1, wherein the deflection surface has a shape selected from the group consisting of substantially planar and curved in a horizontal arc. 3. The aircraft defined in claim 1, wherein the deflector has a curved surface for deflecting the airstream. 4. A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft; (c) a wing on each side of the fuselage, each wing having a front edge, a rear edge and an upper surface extending from the front edge to the rear edge thereof; (d) means for increasing the speed of an airstream flowing over the upper surface of each wing; and (e) an air deflector disposed on each side of the fuselage between the rear edge of each wing and the aircraft tail and having a deflection surface to deflect downward the airstream flowing over the upper surface of the wing, wherein said deflector is retractable into and out of the fuselage, said deflector being movable between a first position within the fuselage and a second position within the airstream. 5. A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft; (c) a wing on-each side of the fuselage, each wing having a front edge, a rear edge and an upper surface extending from the front edge to the rear edge thereof; (d) means for increasing the speed of an airstream flowing over the upper surface of each wing; and (e) an air deflector disposed on each side of the fuselage between the rear edge of each wing and the aircraft tail and having a deflection surface to deflect downward the airstream flowing over the upper surface of the wing, wherein said deflection surface is rotatable about an axis perpendicular to said central longitudinal axis, said deflection surface being rotatable between a first position in which said airstream is minimally deflected and a second position in which the airstream is maximally deflected; and wherein said deflection surface is arranged substantially parallel to the central longitudinal axis when in the first position. 6. The aircraft defined in claim 5, wherein said deflection surface is arranged at a substantial angle to the central longitudinal axis when in the second position. 7. A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft; (c) a wing on each side of the fuselage, each wing having a front edge, a rear edge and an upper surface extending from the front edge to the rear edge thereof; (d) means for increasing the speed of an airstream flowing over the upper surface of each wing; and (e) an air deflector disposed on each side of the fuselage between the rear edge of each wing and the aircraft tail and having a deflection surface to deflect downward the airstream flowing over the upper surface of the wing, wherein each wing has a channel extending from the front edge to the rear edge thereof and defining a channel axis aligned substantially in parallel with said central longitudinal axis of the aircraft, and wherein said means for increasing the speed of the airstream flowing over said upper surface of each wing comprises a propeller arranged to rotate in a plane substantially perpendicular to said central longitudinal axis and about an axis substantially parallel to the channel axis of its associated wing, the plane of rotation of each propeller being substantially adjacent to the rear edge of the wing and the respective channel of its associated wing. 8. A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft; (c) a wing on each side of the fuselage, each wing having a front edge, a rear edge and an upper surface extending from the front edge to the rear edge thereof; (d) means for increasing the speed of an airstream flowing over the upper surface of each wing; and (e) an air deflector disposed on each side of the fuselage between the rear edge of each wing and the aircraft tail and having a deflection surface to deflect downward the airstream flowing over the upper surface of the wing, wherein said means for increasing the speed of the airstream flowing over the upper surface of each wing comprises a plurality of fan blades mounted on and affixed to rotatable shaft that extends substantially perpendicular to the central longitudinal axis. 9. The aircraft defined in claim 8, wherein said means for increasing the speed of the airstream flowing over the upper surface of each wing further comprises a guide member, disposed substantially parallel to said upper surface and adjacent the fan blades, for restricting the airstream to flow in a direction substantially parallel to said upper surface. 10. The aircraft defined in claim 8, wherein each rotatable shaft is disposed within its associated wing. 11. The aircraft defined in claim 8, wherein each shaft and its associated fan blades are rotated by at least one prime mover arranged in the fuselage. 12. The aircraft defined in claim 8, wherein each rotatable shaft is disposed above the upper surface of its associated wing. 13. The aircraft defined in claim 12, wherein each rotatable shaft and its associated fan blades are disposed, in part, in a shroud which covers the blades as they move in the forward direction of the aircraft.
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