| US 7,549,605 B2 | ||
| Electric flight control surface actuation system for aircraft flaps and slats | ||
| Casey Hanlon, Queen Creek, Ariz. (US); Paul T. Wingett, Mesa, Ariz. (US); and Calvin C. Potter, Mesa, Ariz. (US) | ||
| Assigned to Honeywell International Inc., Morristown, N.J. (US) | ||
| Filed on Jul. 29, 2005, as Appl. No. 11/192,622. | ||
| Claims priority of provisional application 60/694640, filed on Jun. 27, 2005. | ||
| Prior Publication US 2006/0289696 A1, Dec. 28, 2006 | ||
| Int. Cl. B64C 13/50 (2006.01) | ||
| U.S. Cl. 244—75.1 [244/213] | 17 Claims |
| 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.
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