[특허]Circulation controlled airfoil

West Virginia University

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색도움말
검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

연합인증

연합인증 가입 기관의 연구자들은 소속기관의 인증정보(ID와 암호)를 이용해 다른 대학, 연구기관, 서비스 공급자의 다양한 온라인 자원과 연구 데이터를 이용할 수 있습니다.

이는 여행자가 자국에서 발행 받은 여권으로 세계 각국을 자유롭게 여행할 수 있는 것과 같습니다.

연합인증으로 이용이 가능한 서비스는 NTIS, DataON, Edison, Kafe, Webinar 등이 있습니다.

한번의 인증절차만으로 연합인증 가입 서비스에 추가 로그인 없이 이용이 가능합니다.

다만, 연합인증을 위해서는 최초 1회만 인증 절차가 필요합니다. (회원이 아닐 경우 회원 가입이 필요합니다.)

연합인증 절차는 다음과 같습니다.

최초이용시에는
ScienceON에 로그인 → 연합인증 서비스 접속 → 로그인 (본인 확인 또는 회원가입) → 서비스 이용

그 이후에는
ScienceON 로그인 → 연합인증 서비스 접속 → 서비스 이용

연합인증을 활용하시면 KISTI가 제공하는 다양한 서비스를 편리하게 이용하실 수 있습니다.

특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Circulation controlled airfoil

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-023/02
미국특허분류(USC)	244/206; 244/210; 416/090.0A; 416/091
출원번호	UP-0387136 (2006-03-22)
등록번호	US-7708229 (2010-06-03)
발명자 / 주소	Angle, II, Gerald M. Smith, James E.
출원인 / 주소	West Virginia University
대리인 / 주소	Thompson Hine LLP
인용정보	피인용 횟수 : 6 인용 특허 : 17

초록
▼

A system and method provides for the manipulation of the aerodynamic characteristics of airfoils and other aerostructures using blowing and/or suction. This system and method uses one or more internal cavities located within an airfoil. An internal cavity is coupled to the exterior surface of the airfoil via one or more slots. A rotary actuator is incorporated into a slot. When the rotary actuator is rotated into a first position, it forms a channel that allows fluid to pass between the internal cavity and the air surrounding the airfoil. When the rotary...

대표
청구항
▼

What is claimed is: 1. A system for modulating the aerodynamic characteristics of an airfoil with an external surface, comprising: An internal cavity located within the external surface; A slot located on the external surface, connecting said internal cavity to the external surface; A rotating assembly inserted into and rotating within said slot with a first orientation and a second orientation; and A channel formed through said rotating assembly with an internal opening to said internal cavity and an external opening to the external surface, wherein said channel allows flow between said internal cavity and the external surface in said first orientation, and said channel substantially prevents flow between said internal cavity and the external surface in said second orientation. 2. A system of claim 1, further comprising a sealing mechanism located within said internal cavity that occludes said channel in part of said first orientation. 3. A system of claim 2, wherein the occlusion of said channel by sealing mechanism creates a third orientation and a fourth orientation, whereby said sealing mechanism blocks said channel in said third orientation preventing flow through said channel between said internal cavity and the external surface of the airfoil, while said channel is not blocked by said sealing mechanism in said fourth orientation thereby allowing flow through said channel between said internal cavity and said external surface of the airfoil. 4. A system of claim 2, whereby a wedge located within said rotating assembly divides said internal opening into two separate inlets. 5. A system of claim 1, wherein said internal cavity is pressurized such that flow through the channel is directed from said internal cavity out to said external surface. 6. A system of claim 1, wherein said slot is located in the leading edge of the airfoil. 7. A system of claim 6, wherein the rotation of said rotating assembly can orient said external opening from −60 degrees to +60 degrees from the centerline of said airfoil. 8. A system of claim 6, further comprising: A second slot located on the surface of the airfoil connecting said internal cavity to the external surface; A second rotating assembly inserted into and rotating within said second slot with an A orientation and a B orientation; and, A second channel formed through said second rotating assembly with an inner opening to said internal cavity and an outer opening to said external surface, wherein said second channel allows flow between said internal cavity and the external surface in said A orientation, and said second channel substantially prevents flow between said internal cavity and the external surface in said B orientation. 9. A system of claim 8, wherein said second rotating assembly is located in the trailing edge of the airfoil. 10. A system of claim 8, wherein said second channel connects a second internal cavity located within the external surface to said external surface. 11. A system of claim 6, further comprising slots located on the upper and lower surfaces of the airfoil, wherein each slot has an open position that allows flow through between said internal cavity and the external surface and a closed position that substantially prevents flow through said internal cavity and the external surface. 12. A system of claim 11, wherein a pair of said slots are located within the first 50% chord of the airfoil. 13. A system of claim 12, wherein said internal cavity is pressurized and said slots are oriented to direct the flow from the internal cavity to the external surface into the relative velocity vector of the freestream air over the external surface. 14. A system of claim 11, wherein said slots are modulated such that flow between said internal cavity and the external surface varies between a minimum in said closed position and a maximum in said open position based on said modulation. 15. A system of claim 11, wherein said slots allows flow between a second internal cavity within the external surface to said external surface. 16. A system of claim 1, further comprising a control means for directing the rotation of said rotating assembly to modulate the aerodynamic characteristics. 17. A helicopter rotor blade control system, comprising: A rotor rotatably mounted to the helicopter; A rotor blade with an exterior, an interior, a leading edge, a trailing edge, and root attached by said root to said rotor; An internal cavity formed in said interior and connected to said rotor such that air can flow between said rotor and said internal cavity; A slot formed in said leading edge creating a channel between said internal cavity through to said exterior; and, A rotary actuator with a first orientation and a second orientation located inside said channel whereby said rotary actuator in said first orientation forms a channel allowing air to flow between said exterior and said internal cavity and when said rotary actuator in said second orientation closes the channel to substantially prevents air from flowing between said exterior and said internal cavity. 18. A system of claim 17, whereby said internal cavity is pressurized with air. 19. A system of claim 17, whereby in said second orientation, said rotary actuator forms a second channel allowing air to flow between said exterior and said internal cavity and said rotary actuator closes said second channel in said first orientation, such that said second channel substantially prevents air from flowing between said exterior and said internal cavity. 20. A system of claim 17, whereby said root is rigidly attached to said rotor. 21. A system of claim 17, whereby said rotary actuator decreases the lift generated by said rotor blade when said rotor blade is in one portion of its rotation around the helicopter and increases lift in the remaining portion of its rotation around the helicopter. 22. A system of claim 17, further comprising slots located on the upper and lower surfaces of the airfoil, wherein each slot has an open position that allows flow through between said internal cavity and the external surface and a closed position that substantially prevents flow through said internal cavity and the external surface.

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 6

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

연합인증

특허 상세정보

Circulation controlled airfoil

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 6

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

연합인증

특허 상세정보

Circulation controlled airfoil

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 6

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼