[특허]Helicopter attitude and airspeed acquisition and retention system

United Technologies Corporation

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

Helicopter attitude and airspeed acquisition and retention system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G06F-015/50 B64C-011/34
미국특허분류(USC)	364/434; 244/017.13; 244/177; 244/178; 364/424
출원번호	US-0176832 (1980-08-08)
발명자 / 주소	Clelford, Douglas H. Murphy, Richard D.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Williams, M. P.
인용정보	피인용 횟수 : 10 인용 특허 : 5

초록
▼

A helicopter pitch axis autopilot system, including airspeed hold at cruise speeds and pitch attitude hold below cruise speeds, includes integrated longitudinal acceleration drift corrected by heavily filtered Pitot static airspeed as a filtered airspeed reference, use of a beeper to nudge the airspeed reference above cruise speeds or the pitch attitude reference below cruise speeds, resynchronizing of airspeed reference, pitch attitude reference, pitch autopilot integrator and stick trim position reference, momentarily in response to airspeed transitions between cruise and sub-cruise speeds or in response to initiation of beeping, and continuously during trim release. Pilot override without disengagement of the autopilot and ultimate return to a previous speed or attitude is achieved by sensing pilot activity and causing the pitch autopilot integrator value to be held during pilot override, and limiting the value of airspeed error that drives the pitch autopilot integrator once the pilot activity has subsided.

대표
청구항
▼

1. An airspeed hold autopilot system for a helicopter having a longitudinal cyclic pitch control stick with a trim release switch disposed thereon, comprising: a trim actuator responsive to electrical signals applied thereto to position the longitudinal cyclic pitch control stick of the helicopter; airspeed means for providing an airspeed signal indicative of actual helicopter airspeed; trim means responsive to said trim release switch for providing a trim release signal; position means responsive to said trim actuator for providing a stick trim position signal indicative of the longitudinal cyclic pitch stick trim position established by said trim actuator; and signal processing means, responsive to said airspeed signal, said trim release signal, and said stick trim position signal, for providing in response to the presence of said trim release signal, an airspeed reference signal equal to said airspeed signal, and a stick synch signal equal to said stick trim position signal, for providing an airspeed error signal as the difference between said airspeed reference signal and said airspeed signal, for providing in the absence of said trim release signal a pitch autopilot command signal as a function of said airspeed error signal, and for providing a stick reference signal as a function of the difference between said pitch autopilot command signal and said stick synch signal and a stick command error signal applied to said trim actuator as a function of the difference between said stick reference signal and said stick trim position signal, whereby said stick command error signal can be zero during said trim release signal when said pitch autopilot command signal is zero valued and said airspeed reference signal is set equal to said actual airspeed signal so that said airspeed error signal consequently is zero valued, while said stick trim position signal retains a finite value indicative of current stick trim position. 2. An airspeed hold autopilot system according to claim 1 further comprising: attitude means for providing an attitude signal indicative of actual aircraft pitch axis attitude; and wherein said signal processing means is responsive to said attitude signal for providing in response to the presence of said trim release signal an attitude reference signal equal to said attitude signal, for providing an attitude error signal as the difference between said attitude reference signal and said attitude signal, for providing in the absence of said trim release signal said pitch autopilot command signal as a function of said airspeed signal whenever the airspeed indicated by said airspeed signal is in excess of a predetermined threshold cruise speed, or as a function of said attitude error signal whenever the airspeed indicated by said airspeed signal is less than said predetermined threshold cruise speed, whereby said stick command error signal can be zero during said trim release signal when said pitch autopilot command signal is zero valued, said airspeed reference signal is set equal to said actual airspeed signal so that said airspeed error signal consequently is zero valued and said attitude reference signal is set to said attitude signal so that said attitude error signal consequently is zero valued, while said stick trim position signal retains a finite value indicative of current stick trim position. 3. A pitch axis autopilot system for a helicopter having a longitudinal cyclic pitch control stick, comprising: a trim actuator responsive to electrical signals applied thereto to position the longitudinal cyclic pitch control stick of the helicopter; attitude means for providing an attitude signal indicative of actual aircraft pitch axis attitude; airspeed means for providing an airspeed signal indicative of actual helicopter airspeed; position means responsive to said trim actuator for providing a stick trim position signal indicative of the longitudinal cyclic pitch stick trim position established by said trim actuator; and signal processing means, responsive to said airspeed signal, said attitude signal, and said stick trim position signal, for providing in response to said airspeed signal, a cruise speed transition signal whenever the airspeed indicated by said airspeed signal transitions from a predetermined threshold cruise speed to a sub-cruise speed or vice versa, for providing in response to the presence of said cruise speed transition signal, an airspeed reference signal equal to said airspeed signal, an attitude reference signal equal to said attitude signal, and a stick synch signal equal to said stick trim position signal, for providing an airspeed error signal as the difference between said airspeed reference signal and said airspeed signal, an attitude error signal as the difference between said attitude reference signal and said attitude signal, for providing in the absence of said cruise speed transition signal a pitch autopilot command signal as a function of said airspeed error signal if said airspeed signal indicates a cruise speed or as a function of said attitude error signal if said airspeed signal indicates a sub-cruise speed, and for providing a stick reference signal as a function of the difference between said pitch autopilot command signal and said stick synch signal and a stick command error signal applied to said trim actuator as a function of the difference between said stick reference signal and said stick trim position signal, whereby said stick command error signal can be zero during said cruise transition signal when said pitch autopilot command signal is zero valued, said airspeed reference signal is set equal to said airspeed signal so that said airspeed error signal consequently is zero valued and said attitude reference signal is set equal to said attitude signal so that said attitude error signal consequently is zero valued, while said stick trim position signal retains a finite value indicative of current stick trim position, whereby transient attitude disturbances, resulting from transitions between cruise and sub-cruise speeds with the pitch axis autopilot engaged, are mitigated. 4. An airspeed hold autopilot system for a helicopter having a longitudinal cyclic pitch control stick with a forward beeper switch and an aft beeper switch disposed thereon, comprising: a trim actuator responsive to electrical signals applied thereto to position the longitudinal pitch control stick of the helicopter; airspeed means for providing an airspeed signal indicative of actual helicopter airspeed; attitude means for providing an attitude signal indicative of actual helicopter attitude; beeper means responsive to said beeper switches for providing in response to operation of either of said beeper switches a ±beep signal, the polarity of which depends on which of said beeper switches is operated; position means responsive to said trim actuator for providing a stick trim position signal indicative of the longitudinal cyclic pitch stick trim position established by said trim actuator; and signal processing means, responsive to said airspeed signal, said attitude signal, said ±beep signal, and said stick trim position signal, for providing in response to initial presence of said ±beep signal, an airspeed reference signal equal to said airspeed signal, an attitude reference signal equal to said attitude signal, and a stick synch signal equal to said stick trim position signal, for thereafter providing in the presence of said ±beep signal said airspeed reference signal as a function of said ±beep signal if said airspeed signal indicates a cruise speed or said attitude reference signal as a function of said ±beep signal if said airspeed signal indicates a sub-cruise speed, and for providing an airspeed error signal as the difference between said airspeed reference signal and said airspeed signal, an attitude error signal as the difference between said attitude reference signal and said attitude signal, a pitch autopilot command signal as a function of said airspeed error signal if said airspeed signal indicates a cruise speed or as a function of said attitude error signal if said airspeed signal indicates a sub-cruise speed, a stick reference signal as a function of the difference between said pitch autopilot command signal and said stick synch signal, and a stick command error signal applied to said trim actuator as a function of the difference between said stick reference signal and said stick trim position signal, whereby said stick command error signal can be zero during initial presence of said ±beep signal when said pitch autopilot command signal is zero valued, said airspeed reference signal is set equal to said airspeed signal so that said airspeed error signal consequently is zero valued and said attitude reference signal is set equal to said attitude signal so that said attitude error signal consequently is zero valued, while said stick trim position signal retains a finite value indicative of current stick trim position, whereby transient attitude disturbances, resulting from beeping of the pitch axis autopilot trim point, are mitigated. 5. A pitch axis autopilot system for a helicopter, comprising: pitch control means including a longitudinal cyclic pitch control stick and a trim actuator responsive to electrical signals applied thereto to position said control stick to a stick trim position; airspeed means for providing an airspeed signal indicative of actual helicopter airspeed; override means responsive to said pitch control means for providing an override signal indicative of said control stick being moved a threshold amount away from said stick trim position; and signal processing means, responsive to said airspeed signal for providing an airspeed reference signal indicative of an airspeed which said autopilot is to hold and an airspeed error signal as the difference between said airspeed reference signal and said airspeed signal, for providing in the absence of said override signal a pitch autopilot integrator signal as a function of the time integral of said airspeed error signal if the magnitude of said airspeed error signal exceeds a predetermined airspeed error limit magnitude or as a function of the time integral of said airspeed limit magnitude if the magnitude of said airspeed error signal is less than said limit magnitude, for providing in the presence of said override signal said pitch autopilot integral signal equal to the pitch autopilot integral signal which existed at the moment said override signal appears, and for providing a stick command signal for application to said trim actuator as a function of said pitch autopilot integral signal. 6. A pitch axis autopilot system according to claim 5 further comprising: attitude means for providing an attitude signal indicative of actual aircraft pitch axis attitude; and wherein said signal processing means is responsive to said attitude signal for providing an attitude reference signal indicative of an attitude which said autopilot is to hold and an attitude error signal as the difference between said attitude reference signal and said attitude signal, for providing in the absence of said override signal, whenever said airspeed signal indicates an airspeed in excess of a predetermined threshold cruise speed, said autopilot integrator signal as a function of said airspeed error signal or said airspeed limit magnitude, or whenever said airspeed signal indicates an airspeed less than said predetermined threshold cruise speed, said pitch autopilot integrator signal as a function of the time integral of said attitude error signal. 7. Apparatus for providing an aircraft airspeed signal comprising: a Pitot static airspeed sensor for providing a raw airspeed signal indicative of the Pitot static indication of the airspeed of the aircraft; a longitudinal accelerometer for providing a longitudinal acceleration signal indicative of the acceleration of the aircraft along its longitudinal axis; and signal processing means for providing an integrated, filtered airspeed signal, for providing an airspeed difference signal as the difference between said raw airspeed signal and said filtered airspeed signal, for providing a proportional airspeed difference signal as a proportional function of said airspeed difference signal, for providing an integral airspeed difference signal as an integral function of said airspeed difference signal, for providing an aircraft acceleration signal as the summation of said proportional airspeed difference signal, said integral airspeed difference signal, and said longitudinal acceleration signal, and for providing said integrated, filtered airspeed signal as the integral of said acceleration signal.

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 (10)

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

Helicopter attitude and airspeed acquisition and retention system

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 (10)

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

Helicopter attitude and airspeed acquisition and retention system

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 (10)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼