[특허]Low speed model following velocity command system for rotary wing aircraft

Low speed model following velocity command system for rotary wing aircraft 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-011/44 G05D-001/10 G05D-001/08
출원번호	US-0751437 (1991-08-28)
발명자 / 주소	Fogler Jr. Donald L. (Milford) Richard James L. (Stratford) Gold Phillip J. (Shelton CT) Glusman Steven L. (Springfield PA)
출원인 / 주소	United Technologies Corporation (Hartford CT 02)
인용정보	피인용 횟수 : 25 인용 특허 : 0

초록 ▼

A helicopter flight control system (21) includes a model following control system architecture which operates in a velocity command mode at low ground speeds. The control system processes information from a variety of helicopter sensors (31) in order to provide a command signal to the main rotor (11

대표청구항 ▼

A helicopter flight control system of the type having a plurality of sensors which provides: rate signals indicative of the helicopter\s pitch and roll rates of change, attitude signals indicative actual bank angle and pitch attitude, and a signal indicative of actual ground speed; a sidearm controller provides a control input signal value indicative of desired ground speed to the system which controls ground speed in response to the control input signal by providing a command signal to the helicopter\s main rotor, the control system comprising: means for providing, for each value of the control input signal, a corresponding signal value indicative of the helicopter desired rate of change about the pitch and roll axes of the helicopter; a feedforward path including inverse model means for providing for each said desired rate of change signal value a feedforward set point signal value indicative of the command to the main rotor required for the helicopter to fly at the desired ground speed; a rate feedback path including means for computing a difference value between said desired rate of change signal value and the corresponding sensed rate of change signal value, and for providing a rate of change error signal value indicative of the difference; an attitude feedback path comprising: means for integrating said desired rate of change signal value to provide a desired attitude signal value; means for computing a difference value between said desired attitude signal value and the corresponding sensed attitude signal value, and for providing an attitude error signal value indicative of the difference; means, having a derivative lag filter, for filtering said desired attitude signal value to provide a washed out signal value; velocity model means, for providing for each value of said washed out signal, a desired ground speed command signal value indicative of the desired helicopter ground speed; means for computing a difference value between said desired ground speed command signal value and the sensed ground speed signal value, to provide a ground speed error signal value indicative of the difference; means for summing said ground speed error signal value and said attitude error signal value to provide a command modifying signal; means for summing said command modifying signal value, said rate error signal value, and said feedforward signal value to provide a command signal; and means for outputting said command signal to the main rotor.

이 특허를 인용한 특허 (25)

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Thornberg Christopher A. ; Cotton Bryan S., Earth-referenced wind adjustment for hovering aircraft.
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Christensen, Kevin Thomas; Shue, Shyhpyng Jack; Caudill, Troy Sheldon, Flight control laws for vertical flight path.
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Salesse-Lavergne, Marc, Flight control system and method for a rotary wing aircraft, enabling it to maintain either track or heading depending on its forward speed.
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Salesse-Lavergne, Marc, Flight control system and method with track maintenance for a rotary wing aircraft.
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Rollet, Philippe, Flying control device for a rotorcraft.
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Gold Phillip J. (Shelton CT) Fogler ; Jr. Donald L. (Milford CT) Dryfoos James B. (Wallingford PA), Inertial velocity command system.
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Gold Phillip J. ; Fogler ; Jr. Donald L., Integrated fire and flight control system for controlling the angle of attack of a rotary wing aircraft.
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Fogler ; Jr. Donald L. (Milford CT) Keller James F. (Media PA), Maintaining attitude error constant in Euler singularity protection.
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Krysinski Thomasz,FRX ; Beroul Frederic Andre Henri,FRX, Method and device for reducing the effect of the vibration generated by the driveline of a helicopter.
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Krysinsky Tomasz,FRX, Method and device for reducing the vibration generated on the structure of a helicopter.
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VanBiervliet, Filip, Method to control the movements of a flight simulator and flight simulator implementing such method.
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McWaters, Mark Wayne; Nielsen, Scott Richard, Power control for propeller-driven aircraft.
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Vialle, Michel, Rotary wing aircraft provided with propulsion means, and a method applied by said aircraft.
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Mercer, John E.; Albion, Nicolas; Bartel, Mark; Feifel, Marc; Marvin, Mark, Rotorcraft autopilot and methods.
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Mercer, John E.; Albion, Nicolas; Bartel, Mark; Feifel, Marc; Marvin, Mark, Rotorcraft autopilot and methods.
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Mercer, John E.; Feifel, Marc; Marvin, Mark; Albion, Nicolas, Rotorcraft autopilot system, components and methods.
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Mercer, John E.; Feifel, Marc; Marvin, Mark; Albion, Nicolas, Rotorcraft autopilot system, components and methods.
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Mercer, John E.; Feifel, Marc; Marvin, Mark; Albion, Nicolas, Rotorcraft autopilot system, components and methods.
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Richardson, Steven D., Tandem rotor wing rotational position control system.
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Gold, Phillip Jeremy; Dryfoos, James B.; Brewer, Roy, Trim augmentation system for a rotary wing aircraft.
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Gold Phillip J. (Shelton CT) Fogler ; Jr. Donald L. (Milford CT) Skonieczny Joseph (Madison CT) Keller James F. (Media PA), Turn coordination inhibit for rotary wing aircraft control system.
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Wittmer, Kenneth S.; Kubik, Stephen, Vehicle heading error compensation.
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Wittmer, Kenneth S.; Kubik, Stephen, Vehicle heading error compensation.
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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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Low speed model following velocity command system for rotary wing aircraft 원문보기

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Low speed model following velocity command system for rotary wing aircraft 원문보기

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이 특허를 인용한 특허 (25)

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