[특허]Leading edge variable camber system and method

The Boeing Company

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 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

Leading edge variable camber system and method

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/50 B64C-009/24 B64C-013/50 B64C-013/00 B64C-013/16
출원번호	US-0034987 (2013-09-24)
등록번호	US-9180962 (2015-11-10)
발명자 / 주소	Moser, Matthew A. Gardner, Mark J. Finn, Michael R. Good, Mark S. Malachowski, Adam P. Thommen, Monica E. Amorosi, Stephen R. Onu, Dan
출원인 / 주소	The Boeing Company
인용정보	피인용 횟수 : 0 인용 특허 : 17

초록

A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.

대표
청구항
▼

1. A system for varying a wing camber, comprising: a flight control computer configured to compute an optimum slat setting based on aircraft state data;a control system communicatively coupled to the flight control computer, the control system including a control device moveable to any one of a plurality of control device positions including a designated control device position selected by the control device for selecting any one of a plurality of corresponding standard flap settings;a leading edge device coupled to a wing of the aircraft;a slat actuation system communicatively coupled to the control system and configured to actuate the leading edge device;the leading edge device configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device; andwherein the control system is configured to automatically command the slat actuation system to move the leading edge device in one of the upward direction and the downward direction to the optimum slat setting response to manual movement of the control device during flight to the designated control device position. 2. The system of claim 1, wherein: the actuation system is configured to actuate the leading edge device in deflection increments of less than approximately one degree. 3. The system of claim 1, wherein: the designated control device position is a cruise position, a climb position, or an approach position. 4. The system of claim 3, wherein: the leading edge device is limited to movement within a deflection angle of less than approximately three degrees in the upward direction and/or a downward direction relative to the retracted position if the control device is in the cruise position. 5. The system of claim 1, wherein: the aircraft state data includes at least one of the following: aircraft gross weight, aircraft center of gravity, Mach number, and altitude. 6. The system of claim 1, wherein: the control system is configured to automatically command the actuation system to periodically reposition the leading edge device according to a slat positioning schedule while the control device is in the designated control device position. 7. The system of claim 6, wherein: the leading edge device includes an inboard slat and an outboard slat; andthe actuation system is configured to actuate the inboard slat independently of the outboard slat. 8. The system of claim 7, wherein: the actuation system includes a variable camber trim unit (VCTU) positioned between the inboard slat and the outboard slat; andthe VCTU configured for differential deployment of the outboard slat and the inboard slat. 9. The system of claim 1, wherein: the leading edge device includes an inboard slat and an outboard slat; andthe control system is further configured to command differential deployment of the inboard slat and the outboard slat to vary the wing camber along a spanwise direction of the wing. 10. The system of claim 1, wherein the leading edge device comprises a slat, the system further comprising: a seal coupled to a lower edge of the slat and extending toward a lower surface of the wing; andthe seal configured to maintain contact with the lower surface of the wing when the slat is moved in the upward direction and/or the downward direction relative to the retracted position. 11. An aircraft, comprising; a flight control computer configured to compute an optimum slat setting based on aircraft state data;a control system communicatively coupled to the flight control computer, the control system including a control device moveable to any one of a plurality of control device positions including a designated control device position selected by the control device for selecting any one of a plurality of corresponding standard flap settings;a wing including a leading edge;a slat coupled to the leading edge;a slat actuation system communicatively coupled to the control system and configured to actuate the slat in an upward direction and a downward direction relative to a retracted position of the slat; andwherein the control system is configured to automatically command the slat actuation system to move the slat in one of the upward direction and the downward direction to the optimum slat setting in response to manual movement of the control device during flight to the designated control device position. 12. A method of varying a wing camber, the method comprising: computing an optimum slat setting based on aircraft state data;manually selecting a designated control device position using a control device in a flight deck of an aircraft, the control device moveable to any one of a plurality of control device positions for selecting any one of a plurality of corresponding standard flap settings; andautomatically actuating a leading edge device of the aircraft in an upward direction to the optimum slat setting relative to a retracted position of the leading edge device in response to manually selecting the designated control device position to reduce a camber of the wing while the aircraft is in flight. 13. The method of claim 12, wherein actuating the leading edge device comprises: actuating the leading edge device in deflection increments of less than approximately One degree. 14. The method of claim 12, wherein the leading edge device comprises a slat coupled to a slat actuation system, the method further comprising: actuating the slat with the slat actuation system in the upward direction and/or a downward direction relative to the retracted position. 15. The method of claim 12, wherein selecting the designated control device position comprises: selecting one of a cruise position, a climb position, and an approach position. 16. The method of claim 12, wherein: the aircraft state data includes at least one of the following; aircraft gross weight, aircraft center of gravity, Mach number, and altitude. 17. The method of claim 16, wherein actuating the leading edge device includes: actuating an inboard slat and an outboard slat coupled to the leading edge; andautomatically commanding, using a control system, a slat actuation system to periodically reposition the inboard slat and the outboard slat according to a slat positioning schedule when the control device is in the designated control device position. 18. The method of claim 12, wherein the leading edge device includes an inboard slat and an outboard slat, the method further comprising: differentially deploying the inboard slat and the outboard slat to vary the wing camber along a spanwise direction. 19. The method of claim 12, wherein the leading edge device includes an inboard slat and an outboard slat, the method further comprising: actuating the outboard slat independently of the inboard slat. 20. The method of claim 15, wherein the leading edge device includes an inboard slat and an outboard slat, the method further comprising: selecting the cruise position;comparing an aircraft gross weight to a threshold value;if the aircraft gross weight exceeds the threshold value, automatically commanding differential deployment of the inboard slat and the outboard slat in a manner causing a decrease in wing lift at an outboard portion of the wing as compared to an inboard portion of the wing; andif the aircraft gross weight does not exceed the threshold value, automatically commanding the inboard slat and the outboard slat to respective positions selected to minimize aerodynamic drag of the wing. 21. The method of claim 15, farther comprising: limiting movement of the loading edge device to within a deflection angle of less than approximately three degrees in each of the upward direction and a downward direction relative to the retracted position it response to selecting the cruise position. 22. The method of claim 12, further comprising: scaling a gap between a lower edge of the leading edge device and a lower surface of the wing while actuating the leading edge device in the upward direction.

인용문헌 (17)

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

Leading edge variable camber system and method

초록

대표
청구항
▼

인용문헌 (17)

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

Leading edge variable camber system and method

초록

대표청구항 ▼

인용문헌 (17)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

대표
청구항
▼