[특허]Disturbance torque compensated three axis yaw control system

Disturbance torque compensated three axis yaw control system 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64G-001/28
출원번호	US-0916734 (1992-07-20)
발명자 / 주소	Stetson Jr. John B. (New Hope PA)
출원인 / 주소	General Electric Co. (East Windsor NJ 02)
인용정보	피인용 횟수 : 28 인용 특허 : 0

초록 ▼

A satellite attitude control system is usable in the absence of any inertial yaw attitude reference, such as a gyroscope, and in the absence of a pitch bias momentum. Both the roll-yaw rigid body dynamics and the roll-yaw orbit kinematics are modelled. Pitch and roll attitude control are conventional. The model receives inputs from a roll sensor, and roll and yaw torques from reaction wheel monitors. The model produces estimated yaw which controls the spacecraft yaw attitude. The model further produces estimates of the constant component of the disturbance torques for compensation thereof.

대표청구항 ▼

An attitude control system for controlling the orientation of a zero momentum satellite relative to a heavenly body, said satellite having gyroscopic freedom in the orbital plane, and deriving orientation references in the absence of operative gyroscopes, comprising: a satellite body defining roll and yaw axes, said yaw axis being Earth pointing, said roll axis being parallel to the satellite motion, said satellite body having yaw and roll body inertias about said yaw and roll axes respectively; first and second reaction wheels mounted on said body, each of said first and second reaction wheels having a component of momentum along the satellite roll and yaw axes, respectively; Earth sensing means mounted on said body for generating signals representing roll attitude of said satellite relative to said heavenly body; first and second reaction wheel driving means coupled to said first and second reaction wheels, respectively, for accelerating said wheels under the control of torque command signals representing torque commands about said satellite yaw and roll axes; first and second tachometer means coupled to said first and second reaction wheels, respectively, for generating speed signals representing the angular velocities of said reaction wheels; roll attitude control means coupled to said Earth sensing means, and to at least one of said first and second reaction wheel driving means for processing said roll attitude error signals with at least proportional and rate compensation of said roll attitude, for generating said torque command signals representing said torque commands about said roll axis, for accelerating at least an associated one of said reaction wheels; yaw attitude control means coupled to at least one of said first and second reaction wheel driving means for processing estimated yaw signals with at least proportional and rate compensation of said yaw attitude, for generating said torque command signals representing said torque commands about said yaw axis, for accelerating at least an associated one of said reaction wheels; roll reaction wheel torque translation means coupled to at least one of said first and second tachometer means for differentiating said speed signals to generate roll reaction wheel torque representative signals; yaw reaction wheel torque translation means coupled to at least one of said first and second tachometer means for differentiating said speed signals to generate yaw reaction wheel torque representative signals; yaw estimating means coupled to said Earth sensing means, to said roll and yaw reaction wheel torque translation means, and to at least one of said first and second reaction wheel driving means, for modelling the linearized roll/yaw orbit kinematics of said satellite, and for additionally modelling the roll/yaw rigid body dynamics of said satellite, and for applying said signals representing roll attitude, and said yaw and roll reaction wheel torque representative signals to said model, for generating and applying signals representing torque commands about said satellite yaw axis, to said at least one of said first and second reaction wheel driving means; disturbance torque estimating means, said disturbance torque estimating means comprising: (a) average speed measuring means coupled to at least one of said first and second tachometer means for producing average speed signals representative of the average speed of said one of said reaction wheels; and (b) scaling means coupled to said average speed measuring means, for scaling said average speed signals by a factor representative of reaction wheel gyroscopic momentum to produce disturbance torque representative signals representing the constant component of the disturbance torque; and summing means coupled to said disturbance torque estimating means and to said yaw estimating means for adding said disturbance torque representative signals to one of said yaw and roll reaction wheel torque representative signals.

이 특허를 인용한 특허 (28)

Weigl, Harald J.; Goodzeit, Neil E.; Ratan, Santosh, Attitude determination system for yaw-steering spacecraft.
상세보기
Smay John W., Bi-directional momentum bias spacecraft attitude control.
상세보기
Bruce N. Eyerly ; John F. Yocum, Jr., Correction of spacecraft steering control law for unexpected orbital inclination effects.
상세보기
Rodden John J. ; Furumoto Nobuo ; Fichter Walter,DEX ; Bruederle Ernst,DEX, Dynamic bias for orbital yaw steering.
상세보기
Goodzeit,Neil Evan; Lempke,James Donald, Efficient orbit sparing system for space vehicle constellations.
상세보기
Potter,Calvin C.; Abel,Stephen G.; Klupar,George J., Energy storage flywheel voltage regulation and load sharing system and method.
상세보기
Heatwole, Craig M.; Herman, Louis K.; Manke, Girard M.; Hamada, Brian T., Fault detection pseudo gyro.
상세보기
Goodzeit, Neil Evan, Fault tolerant attitude control system for zero momentum spacecraft.
상세보기
Moroz,Emilian Mieczyslaw; Pierce,Kirk Gee, Method and apparatus for reducing rotor blade deflections, loads, and/or peak rotational speed.
상세보기
John E. Davis, Method and sensor for capturing rate and position and stabilization of a satellite using at least one focal plane.
상세보기
Surauer Michael,DEX ; Fichter Walter,DEX ; Zentgraf Peter,DEX, Method for controlling the attitude of a three-axis stabilized, earth oriented bias momentum spacecraft.
상세보기
Vandenbussche, Francis; Janvier, Michel Philippe; Van Overbeek, Antonius Josephus Maria; Holt, Antony Philip, Method of controlling or stabilizing the attitude of a vehicle in space.
상세보기
Hamilton, Brian, Methods and systems for efficiently orienting an agile vehicle using a gyroscope array.
상세보기
Shankar Uday J. (Plainsboro NJ) Goodzeit Neil E. (East Windsor NJ) Schmidt ; Jr. George E. (Newtown PA), Minimum propellant, zero momentum spacecraft attitude control system.
상세보기
Nielson Marlin C., Momentum wheel oscillation filter.
상세보기
Tsuji, Shigeru; Fukunaga, Shigeki; Namura, Mitsuhiro; Kawai, Koji; Shirato, Kenichi, Movement direction control apparatus and computer program.
상세보기
Tilley Scott W. ; Holmes Thomas J. ; Reckdahl Keith J., Onboard attitude control using reaction wheels.
상세보기
Herman Louis K. ; Heatwole Craig M. ; Manke Girard M. ; McCain Ian M. ; Hamada Brian T., Pseudo gyro.
상세보기
Herman Louis K. ; Heatwole Craig M. ; Manke Girard M. ; Hamada Brian T., Pseudo gyro with unmodeled disturbance torque estimation.
상세보기
Raymond Charles D'Ambrosio ; Minh Ngoc Tran, Satellite attitude control system.
상세보기
Fowell Richard A. (Culver City CA) Yocum John F. (Rancho Palos Verdes CA), Satellite spin axis stabilization using a single degree of freedom transverse momentum storage device.
상세보기
Richard A. Fowell, Satellite spin reorientation using a single degree of freedom momentum storage device.
상세보기
John E. Davis ; Henry H. Liao, Sensor system and method for determining yaw orientation of a satellite.
상세보기
Cielaszyk David ; Furumoto Nobi ; Machlis Matthew, Spacecraft yaw pointing for inclined orbits.
상세보기
Surauer Michael,DEX ; Roche Christian,DEX ; Fichter Walter,DEX, Sun search method and apparatus for a satellite stabilized in three axes.
상세보기
Spector Victor A., System and method for reducing mechanical disturbances from energy storage flywheels.
상세보기
Goodzeit, Neil E., System for geosynchronous spacecraft rapid earth reacquisition.
상세보기
Goodzeit, Neil E.; Weigl, Harald J., System for on-orbit correction of spacecraft payload pointing errors.
상세보기

내보내기 메뉴

내보내기 구분

파일저장
인쇄
메일전송

구성항목

기본정보
상세정보

관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC

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

AI-Helper ※ AI-Helper는 을 사용합니다.

AI-Helper

안녕하세요, AI-Helper입니다. 좌측 "선택된 텍스트"에서 텍스트를 선택하여 요약, 번역, 용어설명을 실행하세요.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.

IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

연합인증

Disturbance torque compensated three axis yaw control system 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

이 특허를 인용한 특허 (28)

관련 콘텐츠

특허 원문 보기

IPC 상위 출원인

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트

내보내기 구분	파일저장 인쇄 메일전송
구성항목	기본정보 상세정보 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

연합인증

Disturbance torque compensated three axis yaw control system 원문보기

초록 ▼

대표청구항 ▼

연구과제 타임라인

전체(0) 논문(0) 특허(0) 보고서(0)

전체(0) 논문(0) 특허(0) 보고서(0)

이 특허를 인용한 특허 (28)

관련 콘텐츠

특허 원문 보기

IPC 상위 출원인

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트