[특허]Flight control surface actuation system with redundantly configured and lockable actuator assemblies

Honeywell International Inc.

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Flight control surface actuation system with redundantly configured and lockable actuator assemblies

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-013/14 B64C-013/00
미국특허분류(USC)	244/099.3; 244/224
출원번호	UP-0192625 (2005-07-28)
등록번호	US-7607611 (2009-11-10)
발명자 / 주소	Wingett, Paul T. Potter, Calvin C. Hanlon, Casey Benson, Dwayne M.
출원인 / 주소	Honeywell International Inc.
대리인 / 주소	Ingrassia Fisher & Lorenz, P.C.
인용정보	피인용 횟수 : 7 인용 특허 : 15

초록

A flight control surface actuator assembly includes a pair of flight control surface actuators and a pivot arm. One of the flight control surface actuators is coupled to a flight control surface and a static airframe structure, the other flight control surface actuator is coupled to the flight control surface and the pivot arm. The pivot arm coupled to the static airframe structure and is configured to pivot relative to the second flight control surface actuator and the static airframe structure.

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We claim: 1. A flight control surface actuation system, comprising: a first flight control surface actuator adapted to couple to a flight control surface and a static airframe structure, the first flight control surface actuator further adapted to receive a drive force and operable, upon receipt thereof, to move between at least an extended position and a retracted position; a second flight control surface actuator adapted to couple to the flight control surface, the second flight control surface actuator further adapted to receive a drive force and operable, upon receipt thereof, to move between at least an extended position and a retracted position; a pivot arm rotationally coupled to, and configured to pivot relative to, the second flight control surface actuator, and directly rotationally mounted on, and configured to pivot relative to, the static airframe structure; and a pivot arm lock movable between a locked position, in which the pivot arm lock prevents rotation of the pivot arm, and an unlocked position, in which the pivot arm lock does not prevent rotation of the pivot arm. 2. The actuator assembly of claim 1, wherein: the pivot arm includes a first pivot point and a second pivot point; the pivot arm is adapted to be rotationally coupled to the static airframe structure at the first pivot point; and the pivot arm is directly rotationally mounted on the second flight control surface actuator at the second pivot point. 3. The actuator assembly of claim 1, wherein: the first actuator comprises a hydraulic actuator; and the second actuator comprises an electromechanical actuator. 4. The actuator assembly of claim 1, further comprising: first and second drive force control mechanisms, the first and second drive force control mechanisms adapted to receive actuator position commands and operable, upon receipt thereof, to control the drive force supplied to the first and second actuators, respectively. 5. The system of claim 4, wherein: the first actuator comprises a hydraulic actuator; the first drive force control unit comprises a hydraulic fluid control valve; the second actuator comprises an electromechanical actuator; and the second drive force control unit comprises a motor. 6. A flight control surface actuation system, comprising: a movably mounted flight control surface; a first flight control surface actuator coupled to the flight control surface and a static airframe structure, the first flight control surface actuator adapted to receive a drive force and operable, upon receipt thereof, to move the flight control surface between at least an extended position and a retracted position; a second flight control surface actuator coupled to the flight control surface, the second flight control surface actuator adapted to receive a drive force and operable, upon receipt thereof, to move the flight control surface between at least an extended position and a retracted position; and a pivot arm rotationally coupled to, and configured to pivot relative to, the second flight control surface actuator and directly rotationally mounted on, and configured to pivot relative to, the static airframe structure. 7. The system of claim 6, wherein: the pivot arm includes a first pivot point and a second pivot point; the pivot arm is directly rotationally mounted on the static airframe structure at the first pivot point; and the pivot arm is rotationally coupled to the second flight control surface actuator at the second pivot point. 8. The system of claim 6, further comprising: a pivot arm lock movable between a locked position, in which the pivot arm lock prevents rotation of the pivot arm, and an unlocked position, in which the pivot arm lock does not prevent rotation of the pivot arm. 9. The system of claim 6, wherein: the first actuator comprises a hydraulic actuator; and the second actuator comprises an electromechanical actuator. 10. The system of claim 6, further comprising: an actuator controller adapted to receive flight control surface position commands and operable, in response thereto, to supply actuator position commands; and first and second drive force control mechanisms, the first and second drive force control mechanisms adapted to receive actuator position commands and operable, upon receipt thereof, to control the drive force supplied to the first and second actuators, respectively. 11. The system of claim 10, wherein: the first actuator comprises a hydraulic actuator; the first drive force control unit comprises a hydraulic fluid control valve; the second actuator comprises an electromechanical actuator; and the second drive force control unit comprises a motor. 12. The system of claim 10, wherein: the controller is further coupled to receive one or more signals representative of first and second actuator operability and is further operable, in response thereto, to determine if one or both of the first and second actuators are operable; the controller is configured to supply actuator position commands to both the first and second drive force control units if both the first and second actuators are determined to be operable; and the controller is configured to supply actuator position commands to only one of the first and second drive force control units if only the first actuator is determined to be operable. 13. The system of claim 10, wherein the controller is further configured to supply lock commands and wherein the system further comprises: a pivot arm lock coupled to receive the lock commands and operable, upon receipt thereof, to move between a locked position, in which the pivot arm lock prevents rotation of the pivot arm and, and an unlocked position, in which the pivot arm lock does not prevent rotation of the pivot arm. 14. A flight control surface actuation system, comprising: an actuator controller adapted to receive flight control surface position commands and operable, in response thereto, to supply actuator position commands; a first drive force control unit coupled to receive the actuator position commands and operable, upon receipt thereof, to supply a first drive force; a second drive force control unit coupled to receive the actuator position commands and operable, upon receipt thereof, to supply a second drive force; a first flight control surface actuator adapted to couple to a flight control surface and a static airframe structure, the first flight control surface actuator coupled to receive the first drive force and operable, upon receipt thereof, to move between at least an extended position and a retracted position; a second flight control surface actuator adapted to coupled to the flight control surface, the second flight control surface actuator adapted to receive the second drive force and operable, upon receipt thereof, to move between at least an extended position and a retracted position; a pivot arm rotationally coupled to, and configured to pivot relative to, the second flight control surface actuator, and directly rotationally mounted on, and configured to pivot relative to, the static airframe structure; and a pivot arm lock movable between a locked position, in which the pivot arm lock prevents rotation of the pivot arm, and an unlocked position, in which the pivot arm lock does not prevent rotation of the pivot arm. 15. The system of claim 14, wherein: the pivot arm includes a first pivot point and a second pivot point; the pivot arm is adapted to be directly rotationally mounted on the static airframe structure at the first pivot point; and the pivot arm is rotationally coupled to the second flight control surface actuator at the second pivot point. 16. The system of claim 14, wherein: the first actuator comprises a hydraulic actuator; the first drive force control unit comprises a hydraulic fluid control valve; the second actuator comprises an electromechanical actuator; and the second drive force control unit comprises a motor. 17. The system of claim 14, wherein: the controller is further coupled to receive one or more signals representative of first and second actuator operability and is further operable, in response thereto, to determine if one or both of the first and second actuators are operable; the controller is configured to supply actuator position commands to both the first and second drive force control units if both the first and second actuators are determined to be operable; and the controller is configured to supply actuator position commands to only one of the first and second drive force control units if only the first actuator is determined to be operable. 18. The system of claim 14, wherein: the controller is further configured to supply lock commands and the pivot arm lock is coupled to receive the lock commands and is operable, upon receipt thereof, to move between the locked positions and the unlocked positions.

이 특허에 인용된 특허 (15)

이 특허를 인용한 특허 피인용횟수: 7

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특허 상세정보

Flight control surface actuation system with redundantly configured and lockable actuator assemblies

초록

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이 특허에 인용된 특허 (15)

이 특허를 인용한 특허 피인용횟수: 7

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특허 상세정보

Flight control surface actuation system with redundantly configured and lockable actuator assemblies

초록

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이 특허에 인용된 특허 (15)

이 특허를 인용한 특허 피인용횟수: 7

IPC 상위 출원인

과제정보

상세정보조회

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IPC 상세정보(version : 201201)

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