[특허]Rotorcraft fly-by-wire control laws

Bell Helicopter Textron Inc.

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Rotorcraft fly-by-wire control laws

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/00 B64G-001/24 B64C-013/50 B64C-013/04 B64D-043/00 B64C-013/12
출원번호	US-0212689 (2016-07-18)
등록번호	US-9771145 (2017-09-26)
발명자 / 주소	Kim, Sung K. Bothwell, Christopher M. Fortenbaugh, Robert Lee
출원인 / 주소	Bell Helicopter Textron Inc.
인용정보	피인용 횟수 : 1 인용 특허 : 0

초록
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According to one embodiment, a flight control system includes a pilot control assembly and a flight control computer. The pilot control assembly can receive commands from a pilot. The flight control computer can receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer can instruct, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic. The flight control computer can instruct, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system.

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1. A flight control system, comprising: a pilot control assembly configured to receive commands from a pilot, wherein the flight control system is a fly-by-wire flight control system in electrical communication with the pilot control assembly; anda flight control computer is in electrical communication between the flight control system and the pilot control assembly, the flight control computer configured to: receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic;instruct, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic; andinstruct, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system to at least partially offset the expected change to the second flight characteristic such that the flight control system at least partially decouples aircraft motions that are inherently coupled. 2. The flight control system of claim 1, wherein the flight control computer is configured to instruct the flight control module to transmit an instruction to change the second operating condition of the flight control system by instructing the flight control system to transmit an instruction to change the second operating condition by a first amount and then washing out the change to the second operating condition over a period of time. 3. The flight control system of claim 2, wherein the period of time is less than ten seconds. 4. The flight control system of claim 1, wherein: the rotorcraft is operating in a first steady state condition prior to transmitting an instruction to change the first operating condition of the flight control system;the rotorcraft is operating in a second steady state condition after transmitting an instruction to change the first operating condition of the flight control system; andthe flight control computer is configured to instruct the flight control module to transmit an instruction to change the second operating condition of the flight control system by instructing the flight control module to transmit an instruction to change the second operating condition by a first amount and then washing out the change to the second operating condition over a period of time. 5. The flight control system of claim 4, wherein operating in the second steady state comprises returning to the first steady state. 6. The flight control system of claim 1, wherein: the pilot control assembly comprises a pilot control stick and a motor configured to move the pilot control stick in response to commands from the flight control computer; andthe flight control computer is configured to not command the motor to move the pilot control stick in response to instructing the flight control system to change the second operating condition of the flight control system. 7. The flight control system of claim 6, wherein the flight control computer is configured to command the motor to move the pilot control stick based on positions of the swashplate during steady state conditions and is configured to not command the motor to move the pilot control stick during transitory conditions. 8. A method for decoupling motions of a rotorcraft, comprising: receiving, from a pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic;instructing, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic; andinstructing, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system to at least partially offset the expected change to the second flight characteristic such that the flight control system at least partially decouples aircraft motions that are inherently coupled. 9. The method of claim 8, wherein instructing the flight control system to change the second operating condition comprises instructing the flight control system to change the second operating condition by a first amount and then washing out the change to the second operating condition over a period of time. 10. The method of claim 9, wherein the period of time is less than ten seconds. 11. The method of claim 8, wherein: the rotorcraft is operating in a first steady state condition prior to instructing the flight control system to change the first operating condition of the flight control system;the rotorcraft is operating in a second steady state condition after instructing the flight control system to change the first operating condition of the flight control system; andinstructing the flight control system to change the second operating condition comprises instructing the flight control system to change the second operating condition by a first amount and then washing out the change to the second operating condition over a period of time. 12. The method of claim 11, wherein operating in the second steady state comprises returning to the first steady state. 13. The method of claim 8, wherein the pilot control assembly comprises a pilot control stick and a motor configured to move the pilot control stick in response commands to from the flight control computer, the method further comprising: preventing the flight control system from commanding the motor to move the pilot control stick in response to instructing the flight control system to change the second operating condition of the flight control system. 14. The method of claim 13, wherein preventing the flight control system from commanding the motor to move the pilot control stick comprises commanding the motor to move the pilot control stick based on positions of the swashplate during steady state conditions and preventing the flight control system from commanding the motor to move the pilot control stick during transitory conditions.

이 특허를 인용한 특허 피인용횟수: 1

Geiger, Derek; Wulff, Ole; Litwin, Jonathan Aaron; Greenfield, Aaron L.. Rotor speed control using a feed-forward rotor speed command. USP20190110189559.

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Rotorcraft fly-by-wire control laws

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Rotorcraft fly-by-wire control laws

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이 특허를 인용한 특허 피인용횟수: 1

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IPC 상세정보(version : 201201)

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