Electric flight control surface actuation system for aircraft flaps and slats
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-013/50
B64C-013/00
출원번호
UP-0192622
(2005-07-29)
등록번호
US-7549605
(2009-07-01)
발명자
/ 주소
Hanlon, Casey
Wingett, Paul T.
Potter, Calvin C.
출원인 / 주소
Honeywell International Inc.
대리인 / 주소
Ingrassia Fisher & Lorenz, P.C.
인용정보
피인용 횟수 :
14인용 특허 :
24
초록▼
An aircraft flight control surface actuation system includes a plurality of electric motors-driven flap actuators, and a plurality of electric motor-driven slat actuators. The motor-driven actuators receive activation signals from flap and slat actuator controllers and is, in response to the activat
An aircraft flight control surface actuation system includes a plurality of electric motors-driven flap actuators, and a plurality of electric motor-driven slat actuators. The motor-driven actuators receive activation signals from flap and slat actuator controllers and is, in response to the activation signals, move the flaps and slats between stowed and a deployed positions. The flap and slat actuator controllers each include a plurality of independent actuator control channels that independently supply the activation signals to the motor-driven actuators.
대표청구항▼
We claim: 1. A flight control surface actuation system for aircraft having a plurality of flaps and slats on each aircraft wing, the system comprising: a plurality of electric motors, each electric motor coupled to receive activation signals and operable, upon receipt thereof, to supply a drive for
We claim: 1. A flight control surface actuation system for aircraft having a plurality of flaps and slats on each aircraft wing, the system comprising: a plurality of electric motors, each electric motor coupled to receive activation signals and operable, upon receipt thereof, to supply a drive force; a plurality of flap actuators, each flap actuator coupled to receive the drive force from at least one of the electric motors, to thereby move a flap between a stowed and a deployed position; a plurality of slat actuators, each slat actuator coupled to receive the drive force from at least one of the electric motors, to thereby move a slat between a stowed and a deployed position; and a flap actuator controller including a plurality of independent flap actuator control channels and a single spare flap actuator control channel, each flap actuator control channel of the plurality of independent flap actuator control channels (i) exclusively coupled to at least one of the plurality of electric motors that supplies the drive force to a particular flap actuator and (ii) configured to supply the activation signals thereto, the single spare flap actuator control channel coupled to all of the plurality of electric motors on one aircraft wing; and a slat actuator controller including a plurality of independent slat actuator control channels and a single spare slat actuator control channel, each slat actuator control channel of the plurality of independent slat actuator control channels (i) exclusively coupled to at least one of the plurality of electric motors that supplies the drive force to a particular slat actuator and (ii) configured to supply the activation signals thereto, the single spare slat actuator control channel coupled to all of the plurality of electric motors on one aircraft wing. 2. The system of claim 1, wherein each flap actuator is coupled to receive the drive force supplied from two electric motors. 3. The system of claim 2, wherein each flap actuator control channel is coupled to two electric motors, whereby each flap actuator has one flap actuator control channel associated therewith. 4. The system of claim 2, wherein: each flap actuator control channel is coupled to only one electric motor, whereby each flap actuator has two flap actuator control channels associated therewith; and each flap actuator controller is configured such that one of the flap actuator control channels associated with each flap actuator is active and the other flap actuator control channel associated with each flap actuator is inactive. 5. The system of claim 2, wherein: each flap actuator control channel is coupled to only one electric motor, whereby each flap actuator has two flap actuator control channels associated therewith; and each flap actuator controller is configured such that both of the flap actuator control channels associated with each flap actuator are active. 6. The system of claim 2, further comprising: a plurality of drive mechanisms, each drive mechanism coupled between two flap actuators. 7. The system of claim 2, further comprising: a plurality of speed-sum gear assemblies, each speed-sum gear assembly having two inputs and two outputs, each speed-sum gear assembly input coupled to receive the drive force from two electric motors, each speed-sum gear assembly output coupled to supply the received drive force to one of the flap actuators. 8. The system of claim 7, further comprising: a plurality of drive mechanisms, each drive mechanism coupled between a speed-sum gear assembly outputs and a flap actuator. 9. The system of claim 8, wherein each drive mechanism comprises a flexible shaft. 10. The system of claim 8, wherein each drive mechanism comprises a torque tube. 11. The system of claim 1, wherein each slat actuator is coupled to receive the drive force supplied from two electric motors. 12. The system of claim 11, wherein each slat actuator control channel is coupled to two electric motors, whereby each slat actuator has one slat actuator control channel associated therewith. 13. The system of claim 11, wherein: each slat actuator control channel is coupled to only one electric motor, whereby each slat actuator has two slat actuator control channels associated therewith; and each slat actuator controller is configured such that one of the slat actuator control channels associated with each slat actuator is active and the other slat actuator control channel associated with each slat actuator is inactive. 14. The system of claim 11, wherein: each slat actuator control channel is coupled to only one electric motor, whereby each slat actuator has two flap actuator control channels associated therewith; and each slat actuator controller is configured such that both of the slat actuator control channels associated with each slat actuator are active. 15. The system of claim 1, wherein: each flap actuator is a linear actuator; and each slat actuator is a rotary actuator. 16. The system of claim 1, wherein: at least two flap actuators are coupled to a single flap; and at least two slat actuators are coupled to a single slat. 17. The system of claim 1, wherein: each flap actuator controller is associated with one of the aircraft wings; and each slat actuator controller is associated with one of the aircraft wings.
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이 특허에 인용된 특허 (24)
Andrew E. Uttley GB; Peter William Chambers GB; Nigel Blackwell GB; Brian Weller GB, Actuator system for aerospace controls and functions.
Degenholtz, Arthur; Mayer, Edward; Vaghela, Naresh P., Arrangement and associated system having an actuator and a tubular flap-drive member about the actuator.
White Albert H. (Wethersfield CT) Peck Robert E. (Prospect CT) Meyer Gene A. (W. Simsbury CT) Devanney Raymond H. (Winsted CT), Dual stepper motor actuator for fuel metering valve.
Lindstrom Jeffrey V. ; Reed R. David ; Platin Bradley E. ; Beyer Kevin W. ; Reusch David C., Method and apparatus for detecting skew and asymmetry of an airplane flap.
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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