System and method for reducing the noise of pusher type aircraft propellers
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0111414
(2011-05-19)
|
등록번호 |
US-8622334
(2014-01-07)
|
발명자
/ 주소 |
- Drela, Mark
- Gundlach, John
- Parks, Robert
- Ehrmantraut, Adam Scott
|
출원인 / 주소 |
- Aurora Flight Sciences Corporation
|
대리인 / 주소 |
Katten Muchin Rosenman LLP
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
9 |
초록
▼
A system and method for reducing the noise penalty of a pusher propeller, allowing an aircraft to retain its advantages for UAV configurations, while allowing acoustic performance similar to that of a tractor propeller by reducing, or eliminating, propeller noise emissions. The system and method pro
A system and method for reducing the noise penalty of a pusher propeller, allowing an aircraft to retain its advantages for UAV configurations, while allowing acoustic performance similar to that of a tractor propeller by reducing, or eliminating, propeller noise emissions. The system and method provide an airfoil-shaped flight surface with (i) a scoop configured to route boundary layer air and associated wake from said flight surface, and (ii) a suction device configured to provide a suction pressure, wherein the scoop routes boundary layer air from the flight surface to the suction device via an opening in the flight surface.
대표청구항
▼
1. Apparatus for reducing aircraft pusher propeller noise, comprising: an airfoil-shaped flight surface disposed upstream of the pusher propeller;a flight control surface coupled to said flight surface via a hinge;a scoop configured to route boundary layer air from said flight surface, the scoop bei
1. Apparatus for reducing aircraft pusher propeller noise, comprising: an airfoil-shaped flight surface disposed upstream of the pusher propeller;a flight control surface coupled to said flight surface via a hinge;a scoop configured to route boundary layer air from said flight surface, the scoop being disposed at the hinge, the flight control surface being thicker than the flight surface in a direction orthogonal to a longitudinal axis of said hinge; anda suction device configured to provide a suction pressure, and wherein said scoop routes boundary layer air from said flight surface to said suction device. 2. The apparatus of claim 1, wherein the airfoil is shaped to form a portion of said scoop. 3. The apparatus of claim 1, wherein the airfoil-shaped flight surface and the suction device are configured to operate in different modes. 4. The apparatus of claim 1, wherein the suction device develops the suction pressure by at least one of: (i) a shaft driven by the propeller; (ii) an electric motor; (iii) an hydraulic motor; or (iv) one or more combinations thereof. 5. The apparatus of claim 1, wherein air from the boundary layer is provided for engine cooling. 6. The apparatus of claim 1, wherein the suction pressure is applied at at least one of: (i) a control surface hinge line; (ii) an airfoil trailing edge; or (iii) one or more combinations thereof. 7. The apparatus of claim 1, wherein airfoil pressure distribution is configured through airfoil shape to minimize wake development aft of said opening. 8. The apparatus of claim 1 further comprising more than one flight control surface. 9. The apparatus of claim 8, wherein said flight control surface is disposed upstream of the pusher propeller, and wherein a second flight control surface is not disposed upstream of the pusher propeller. 10. The apparatus of claim 9, wherein the flight control surface is configurable in flight to be locked or unlocked from a position to minimize wake caused by deflection of the flight control surface. 11. A method for reducing pusher propeller noise comprising the steps of: routing boundary layer air via a scoop from an airfoil-shaped flight surface that is upstream of the pusher propeller, the flight surface being coupled to a flight control surface via a hinge, the scoop being formed by a space between the flight surface and the flight control surface;applying a suction pressure via an opening in said flight surface; andproviding said suction pressure via a suction device, wherein said scoop routes boundary layer air from said flight surface to said suction device. 12. The method of claim 11, wherein the scoop is integrated into the airfoil is shape. 13. The method of claim 11, wherein the suction device and the airfoil-shaped flight surface are configured to operate in different modes. 14. The method of claim 11, wherein the suction device develops the suction pressure by at least one of: (i) a shaft driven by the propeller; (ii) an electric motor; (iii) an hydraulic motor; or (iv) one or more combinations thereof. 15. The method of claim 11, wherein air from the boundary layer is used for engine cooling. 16. The method of claim 11, wherein suction pressure is applied at at least one of: (i) a control surface hinge line; (ii) an airfoil trailing edge; or (iii) one or more combinations thereof. 17. The method of claim 11, wherein airfoil pressure distribution is configured through airfoil shape to minimize wake development aft of said opening. 18. The apparatus of method 11 further comprising more than one flight control surface. 19. The apparatus of method 18, wherein the flight control surface is upstream of the pusher propeller, and wherein a second flight control surface is not upstream of the pusher propeller. 20. The apparatus of method 19, wherein the flight control surface is configurable in flight to be locked or unlocked from a position to minimize wake due to deflection of the flight control surface. 21. A airfoil-shaped flight surface for reducing pusher propeller noise comprising: a flight control surface coupled to said flight surface at a hinge;a scoop configured to route boundary layer air, the scoop formed by a space disposed between the flight control surface and the flight surface, the flight control surface being thicker than the flight surface in a direction orthogonal to a longitudinal axis of said hinge; anda suction device configured to provide a suction pressure wherein said scoop routes boundary layer air from said flight surface to said suction device.
이 특허에 인용된 특허 (9)
-
Adamson Arthur P. (Cincinnati OH) Gliebe Philip R. (Cincinnati OH), Aircraft propeller noise reduction.
-
Gliebe Philip R. (Cincinnati OH) Majjigi Rudramuni K. (Cincinnati OH), Aircraft pylon.
-
Gordon Bruce J. (Cincinnati OH), Aircraft pylon.
-
Metzger Frederick B. (Simsbury CT) Magliozzi Bernard (West Suffield CT), Cabin noise suppression in propeller driven aircraft.
-
Brewer George D. (San Marcos CA) Marshall David P. (Powder Springs GA), Combination boundary layer control system for high altitude aircraft.
-
Magliozzi Bernard (West Suffield CT) Hanson Donald B. (Broad Brook CT), Engine exhaust/blade interaction noise suppression.
-
Jacobs Loyd D. (Bellevue WA) Shivashankara Belur N. (Bellevue WA), Mounting assembly for unducted prop engine and method.
-
Borchers, Ingo Udo; Haeusler, Sigurd; Bauer, Michael; Drobietz, Roger; Gleine, Wolfgang, Process and apparatus for noise reduction in multi-engine propeller-driven aircraft.
-
Owens Phillip R. (1417 Kirby St. ; NE. Albuquerque NM 87112), V/STOL aircraft and method.
이 특허를 인용한 특허 (2)
-
Kelaidis, Manousos, Method for controlling rotorcraft airfoil to minimize auxiliary rotor noise and enhance rotorcraft performance.
-
Sugaya, Shunji, Uninhabited airborne vehicle and method of controlling the same.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.