[특허]Apparatus and method for determining information for aircraft

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

Apparatus and method for determining information for aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G08B-023/00
미국특허분류(USC)	340/963; 340/969; 073/180
출원번호	US-0861699 (2001-05-21)
발명자 / 주소	Frantz, James B.
대리인 / 주소	Dorsey &
인용정보	피인용 횟수 : 9 인용 특허 : 6

초록
▼

The present invention provides a method for determining information for an air vehicle including the steps of providing a first coefficient of pressure data point, providing a situation involving the air vehicle, deriving pressures during the situation and deriving a second coefficient of pressure data point from the pressures derived during the situation, and defining a line passing through the first and second coefficient of pressure data points, whereby a selected coefficient of pressure data point on the line corresponds to the information. The inven...

대표
청구항
▼

1. A method for determining information for an air vehicle comprising the steps of:providing a first coefficient of pressure data point; providing a situation involving the air vehicle, deriving pressures during the situation and deriving a second coefficient of pressure data point from the pressures derived during the situation; and defining a line passing through the first and second coefficient of pressure data points, whereby a selected coefficient of pressure data point on the line corresponds to the information. 2. The method according to claim 1, wherein the information comprises flight information.3. The method according to claim 1, wherein providing the first coefficient of pressure data point comprises assuming the first coefficient of pressure data point.4. The method according to claim 2, wherein the flight information comprises angle from zero lift.5. The method according to claim 2, wherein the flight information comprises angles from zero yaw.6. The method according to claim 2, wherein the flight information relates to a selected air vehicle configuration.7. The method according to claim 1, further comprising an additional data point, said data points defining a curvilinear relation between coefficients of pressure and the information.8. A method of determining aircraft information for an air vehicle comprising the steps of:creating a zero yaw situation, deriving pressures during the zero yaw situation, and deriving a first coefficient of pressure data point from the pressures derived during the zero yaw situation; creating a yaw producing situation, deriving pressures during the yaw producing situation and deriving a second coefficient of pressure data point from the pressures derived during the yaw producing situation; and defining a line passing through the first and second coefficient of pressure data points, whereby a selected coefficient of pressure data point on the line corresponds to the aircraft information. 9. The method according to claim 8, further comprising pressure sensors including an airfoil pressure sensor operably carried by an airfoil of the air vehicle, a pitot pressure sensor and a static pressure sensor.10. The method according to claim 9, wherein deriving the first and second pressure data points comprises obtaining an airfoil differential pressure from the airfoil pressure sensor and dividing said airfoil differential pressure by a pitot static differential pressure obtained from the pitot and static pressure sensors.11. A method of determining angular deviations from a zero yaw angle for an air vehicle including an airfoil comprising the steps of:providing the air vehicle with pressure sensors operably linked to a microprocessor; performing a zero yaw flight maneuver to provide the zero yaw angle and sensing pressures during the zero yaw flight maneuver; using the microprocessor to derive a coefficient of pressure from the sensed pressures and recording said coefficient of pressure in the microprocessor; acquiring a coefficient of pressure data point while the air vehicle is producing yaw, communicating the coefficient of pressure data point to the microprocessor to define a unique relationship between the coefficient of pressure; and providing an angular deviation from the zero yaw angle for any coefficient of pressure. 12. The method according to claim 11, further comprising providing angular deviation information to a pilot of the air vehicle.13. The method according to claim 12, further comprising providing warnings to the pilot when an angle from zero yaw is approaching an angle at which airflow separates from the airfoil.14. An apparatus for measuring and displaying aircraft information for aircraft with an airfoil and with a pitot pressure sensor and a static pressure sensor comprising:an airfoil pressure sensor on a surface of the airfoil for sensing a local airfoil pressure; a microprocessor operably coupled to the pitot and static pressure sensors and to said airfoil pressure sensor for receiving and processing sensed pressures, for recording a first coefficient of pressure and a second coefficient of pressure, wherein the microprocessor processes and correlates said first and second coefficients of pressure to provide the aircraft information; and an electrical indicator operably coupled to the microprocessor for communicating the information. 15. A method of determining information for an aircraft comprising the steps of:providing first input data; providing second input data; and processing said first input data and said second input data according to a predetermined set of instructions to determine a third data point. 16. The method according to claim 15, wherein the third data point correlates to the information.17. The method according to claim 15, wherein providing said second input data comprisesflying the aircraft. 18. The method according to claim 15, wherein said providing said first input data is selected from the group comprising flying the aircraft, simulating the flying of the aircraft or assuming the first input data.19. The method according to claim 15, wherein the information comprises flight information.20. The method according to claim 15, wherein said processing is carried out by a microprocessor.21. A method of calibrating an aircraft sensor for providing aircraft information, comprising:providing a zero coefficient of pressure data point; and providing an aircraft situation, obtaining a pressure reading during the aircraft situation and deriving a second coefficient of pressure data point from the pressure reading obtained during the aircraft situation. 22. The method according to claim 21, further comprising using the zero coefficient of pressure data point and the second coefficient of pressure data point to define a line, whereby a selected coefficient of pressure data point on the line corresponds to the aircraft information.23. The method according to claim 22, wherein said providing a zero coefficient of pressure data point comprises creating a zero yaw situation and obtaining pressures during the zero yaw situation.24. The method according to claim 22, wherein said providing a zero coefficient of pressure data point comprises creating a zero lift situation and obtaining pressures during the zero lift situation.25. The method according to claim 21, wherein an aircraft carrying the aircraft sensor has a variable configuration.26. The method according to claim 21, wherein an aircraft carrying the aircraft sensor has at least two configurations, and wherein the method may be performed at two selected configurations, the method further comprising interpolating for configurations other than said two selected configurations.27. The method according to claim 26, wherein said two selected configurations comprise flap settings.

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 9

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

Apparatus and method for determining information for aircraft

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 9

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

Apparatus and method for determining information for aircraft

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (6)

이 특허를 인용한 특허 피인용횟수: 9

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼