Systems and methods for attenuation of noise and wakes produced by aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-021/04
B64C-021/08
B64C-009/38
B64C-023/06
출원번호
US-0099400
(2013-12-06)
등록번호
US-9371132
(2016-06-21)
발명자
/ 주소
Shmilovich, Arvin
Khodadoust, Abdollah
출원인 / 주소
The Boeing Company
대리인 / 주소
Ostrager Chong Flaherty & Broitman P.C.
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
Systems and methods for reducing the trailing vortices and lowering the noise produced by the side edges of aircraft flight control surfaces, tips of wings and winglets, and tips of rotor blades. A noise-reducing, wake-alleviating device is disclosed which incorporates an actuator and one or more ai
Systems and methods for reducing the trailing vortices and lowering the noise produced by the side edges of aircraft flight control surfaces, tips of wings and winglets, and tips of rotor blades. A noise-reducing, wake-alleviating device is disclosed which incorporates an actuator and one or more air-ejecting slot-shaped openings coupled to that actuator and located on the upper and/or lower surfaces and/or the side edges of an aircraft flight control surface or the tip of a wing, winglet or blade. The actuation mechanism produces sets of small and fast-moving air jets that traverse the openings in the general streamwise direction. The actuation destabilizes the flap vortex structure, resulting in reduced intensity of trailing vortices and lower airplane noise.
대표청구항▼
1. An aircraft comprising an aerodynamic element, a source of pressurized air, an air jet actuator and a controller, wherein: said aerodynamic element comprises a side edge, upper and lower surfaces, a first slot and a second slot, said first slot being located on one of said upper surface, said low
1. An aircraft comprising an aerodynamic element, a source of pressurized air, an air jet actuator and a controller, wherein: said aerodynamic element comprises a side edge, upper and lower surfaces, a first slot and a second slot, said first slot being located on one of said upper surface, said lower surface or said side edge, and said second slot being located on one of said upper surface, said lower surface or said side edge on which said first slot is not located;said air jet actuator comprises a rotatable element, said rotatable element comprising an interior duct and a helical slot in fluid communication with said interior duct; andsaid controller is operable to cause said interior duct of said rotatable element to be placed in fluid communication with said pressurized air source and also cause said rotatable element to rotate, as a result of which said interior duct of said rotatable element is concurrently in fluid communication with said first and second slots of said aerodynamic element via said helical slot in said rotatable element, thereby enabling pressurized air from said source to exit said first and second slots of said aerodynamic element in the form of respective air jets, wherein said helical slot of said rotating rotatable element causes said respective air jets to traverse said first and second slots respectively. 2. The aircraft as recited in claim 1, wherein each air jet moves along at least a portion of the length of the first slot in a streamwise direction for a distance that is greater than a width of the air jet during rotation of said rotatable element relative to said aerodynamic element. 3. The aircraft as recited in claim 1, further comprising a non-rotatable element comprising an interior duct and an opening in fluid communication with said interior duct of said non-rotatable element and an exterior of said non-rotatable element, wherein said rotatable element and said non-rotatable element are mutually concentric, and said first slot of said aerodynamic element is in fluid communication with said opening of said non-rotatable element. 4. The aircraft as recited in claim 3, wherein said rotatable element is disposed within said interior duct of said non-rotatable element. 5. The aircraft as recited in claim 1, further comprising a valve which, in an open state, allows fluid communication between said interior duct of said rotatable element and said pressurized air source, the state of said valve being controlled by said controller. 6. The aircraft as recited in claim 1, further comprising: a motor which, when activated, causes said rotatable element to rotate, the activation of said motor being controlled by said controller. 7. The aircraft as recited in claim 1, wherein said aerodynamic element is one of the following: a flight control surface, a winglet, a wing of an airplane or a blade of a rotorcraft. 8. The aircraft as recited in claim 7, wherein said side edge comprises one of the following: a side edge of a flight control surfaces, a tip of an airplane wing or winglet, and a tip of a rotorcraft blade. 9. An aircraft comprising an aerodynamic element, a source of pressurized air, an air jet actuator and a controller, wherein said aerodynamic element comprises a side edge and a first slot located on or near the side edge and generally aligned with a streamwise direction; said air jet actuator comprises a rotatable element, said rotatable element comprising an interior duct and a multiplicity of openings in fluid communication with said interior duct; and said controller is operable to cause said interior duct of said rotatable element to be placed in fluid communication with said pressurized air source and also cause said rotatable element to rotate, as a result of which said interior duct of said rotatable element is in fluid communication with said opening of said aerodynamic element via at least one of said multiplicity of openings in said rotatable element, thereby enabling pressurized air from said source to exit said opening of said aerodynamic element in the form of an air jet, and each of said multiplicity of openings of said rotatable element causes a respective air jet to be ejected from said first slot each time that opening comes into a state of fluid communication with said first slot during rotation of said rotatable element, wherein said multiplicity of openings of said rotatable element are circumferentially and axially distributed on a surface of said rotatable element so that successive air jets are produced at successive locations along a length of said opening of said aerodynamic element during rotation of said rotatable element, each air jet being displaced in a first streamwise direction relative to a next air jet. 10. The aircraft as recited in claim 9, wherein said multiplicity of openings of said rotatable element are arranged along a helical line of constant or varying pitch. 11. The apparatus as recited in claim 9, wherein said aerodynamic element is one of the following: a flight control surface, a winglet, a wing of an airplane or a blade of a rotorcraft. 12. An apparatus comprising an aerodynamic element, an air jet actuator and a non-rotatable element, wherein: said aerodynamic element comprises a side edge, a first slot located on said side edge, an upper surface, a second slot located on said upper surface, a lower surface, and a third slot located on said lower surface;said air jet actuator comprises a rotatable element, said rotatable element comprising an interior duct and a slot configured to follow a line that winds around said rotatable element and in fluid communication with said interior duct, wherein said interior duct of said rotatable element is in fluid communication with said slot of said aerodynamic element via said slot of said rotatable element during rotation of said rotatable element relative to said aerodynamic element, and further wherein respective portions of said slot of said rotatable element are concurrently in fluid communication with respective portions of said first, second and third slots of said aerodynamic element during air ejection; andsaid non-rotatable element comprises an interior duct and first through third slots in fluid communication with said interior duct and an exterior of said non-rotatable element, wherein said rotatable element and said non-rotatable element are mutually concentric, and said first through third slots of said aerodynamic element are respectively in fluid communication with said first, second and third slots of said non-rotatable element. 13. The apparatus as recited in claim 12, wherein said aerodynamic element is one of the following: a flight control surface, a winglet, a wing of an airplane or a blade of a rotorcraft. 14. The apparatus as recited in claim 12, further comprising a source of pressurized air, a motor which, when activated, causes said rotatable element to rotate, and a controller which is operable to cause said interior duct of said rotatable element to be placed in fluid communication with said pressurized air source and also cause said rotatable element to rotate, thereby enabling pressurized air from said source to exit said opening of said aerodynamic element in the form of an air jet. 15. The apparatus as recited in claim 14, wherein each air jet moves along at least a portion of the length of the slot in a streamwise direction for a distance that is greater than a width of the air jet during rotation of said rotatable element relative to said aerodynamic element.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (5)
Taylor Robert M. (Vienna VA), Aerodynamic surface tip vortex attenuation system.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.