[특허]Fail-safe dual channel automatic pilot with maneuver limiting

Fail-safe dual channel automatic pilot with maneuver limiting 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05B-009/03
출원번호	US-0558582 (1975-03-17)
발명자 / 주소	Miller Harry (Scottsdale AZ)
출원인 / 주소	Sperry Rand Corporation (New York NY 02)
인용정보	피인용 횟수 : 28 인용 특허 : 0

초록 ▼

Two substantially identical servo channels, coupled through a differential mechanism, position an attitude control surface of an aircraft in response to a common command signal applied to both channels. The common command is coupled to each channel through separate displacement and rate limiting devices to limit the attitude displacement and rate of change of attitude commands about the associated aircraft axis. In the pitch axis a separate normal accelerometer controls each command rate limit so as to prevent excessive pitch maneuvers due to the common command source. Redundant polarity comparators are included for comparing the polarity of the incremental load factor with the polarity of each servo channel output and for applying a brake to clamp the output of a failed servo channel when the polarity of the incremental load factor agrees with the servo motion direction and the incremental load factor exceeds a predetermined level, thus allowing the valid servo to assume control of the aircraft for a limited time until the pilot disconnects the system in response to monitoring circuits which operate alerting devices.

대표청구항 ▼

A control system for controlling the movement of the pitch attitude control surface of an aircraft comprising a common command signal source, first and second substantially identical servo channels coupled to said common command signal source for providing first and second servo outputs respectively in response to said common command signal, summing means responsive to said first and second servo outputs and coupled between said first and second servo channels and said pitch attitude control surface for controlling the movement thereof in accordance with the algebraic sum of said first and second servo outputs, feedback means responsive to said first and second servo outputs for providing feedback signals to said first and second servo channels, whereby movement of said pitch attitude control surface caused by a failure in one said servo channel tends to be compensated by movement of the output of the other said servo channel to minimize undesired maneuvers of said aircraft, first and second limiter means coupled between said common command signal source and said first and second servo channels respectively for limiting said common command signal in Each said channel to minimize undesired maneuvers of said craft when a failure occurs in said common command signal source, said first and second limiter means each comprising rate limiter means for limiting the rate of change of said command signal applied to said first and second servo channels respectively, thereby limiting the rate of change of attitude of said craft in response to said command signal, and first and second normal accelerometer means for providing respective incremental load factor signals representative of the incremental load factor on said aircraft.

이 특허를 인용한 특허 (28)

Villano, William E.; Gibbons, Kevin; Jones, Teddy L.; Recck, Francis W., Actuation control system.
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Boorman, Daniel J.; Griffin, III, John C.; Gunn, Peter D.; Mumaw, Randall J., Apparatuses and methods for displaying and receiving tactical and strategic flight guidance information.
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Boorman, Daniel J.; Griffin, III, John C.; Gunn, Peter D.; Mumaw, Randall J., Apparatuses and methods for displaying and receiving tactical and strategic flight guidance information.
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Boorman, Daniel J.; Griffin, III, John C.; Gunn, Peter D.; Mumaw, Randall J., Apparatuses and methods for displaying and receiving tactical and strategic flight guidance information.
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Boorman, Daniel J.; Griffin, III, John C.; Gunn, Peter D.; Mumaw, Randall J., Apparatuses and methods for displaying and receiving tactical and strategic flight guidance information.
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Boorman, Daniel J.; Gunn, Peter D.; Griffin, III, John C., Apparatuses and methods for displaying autoflight information.
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Boorman, Daniel J.; Gunn, Peter D.; Griffin, III, John C., Apparatuses and systems for controlling autoflight systems.
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Ek Anders (Chicago IL) Hegardt Johan (Buffalo Grove IL), Delayed safety braking apparatus for a servomotor control system.
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Tawfik David A. (Woodcliff Lake NJ) Doniger Jerry (Montvale NJ) Porawski Donald J. (Cedar Grove NJ), Digital flight guidance system.
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Clark, Samuel T.; Johnson, Keith L.; Neff, Andrew D.; Bowe, Roglenda R., Display of taxi route control point information.
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Barrett Jack E. J. (Waupaca WI), Door operator system using counter circuit for determining limit positions.
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Osder Stephen S. (Scottsdale AZ), Dual servo automatic pilot with improved failure monitoring.
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Osder Stephen S. (Scottsdale AZ), Dynamic equalization system for dual channel automatic pilot.
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Hanlon, Casey; Wingett, Paul T.; Potter, Calvin C., Electric flight control surface actuation system for aircraft flaps and slats.
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Buus Henning (Woodinville WA), Electronic controller.
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Bartlett Larry A. (Phoenix AZ) Campbell Curtis M. (Phoenix AZ) Tesdal Ronald I. (Phoenix AZ), Fail operational dual electromechanical servo actuator for aircraft with model monitoring.
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DeWalt ; Michael P., Fail passive dual servo with continuous motor speed and acceleration and monitoring.
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Richter, Martin; Fleddermann, Andreas, Fault-tolerant actuating system for adjusting flaps of an aircraft, comprising adjustment kinematics with a fixed pivot, and a method for monitoring an actuating system.
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Walter, Alexander, Fault-tolerant electromechanical actuating device.
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Takeshi Tomio JP; Hideki Shirasaya JP; Shigeru Tobari JP; Ikuo Sudo JP; Yoshiharu Kubo JP, Flight control apparatus for helicopters.
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Collins, Andrew J., Flight control surface actuation system.
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Takats Imre J. (Bellevue WA), Flight control system employing three controllers operating a dual actuator.
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Kawasaki Josho (Tokyo JPX), Overload prevention apparatus for jacking system of offshore structures.
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Nixon, John M., Rate based autopilot system.
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Thuy Pham D. (Chatenay Malabry FRX), Self-monitored process control device.
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Kubo Yoshiharu,JPX ; Tomio Takeshi,JPX, Servo actuator apparatus and aircraft control apparatus.
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Sabnis, Rohini, Servo transparency warning system and method.
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Clark, Samuel T.; Bowe, Roglenda R.; Jones, Wayne R., System and method for taxi route entry parsing.
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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

내보내기 구분	파일저장 인쇄 메일전송
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저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
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연합인증

Fail-safe dual channel automatic pilot with maneuver limiting 원문보기

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Fail-safe dual channel automatic pilot with maneuver limiting 원문보기

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연구과제 타임라인

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이 특허를 인용한 특허 (28)

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