Electric flight control surface actuation system for aircraft flaps and slats
First 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 plurality of flap actuator controllers, each flap actuator controller including a plurality of independent flap actuator control channels, each flap actuator control channel (i) coupled to at least one of the electric motors that supplies the drive force to a flap actuator and (ii) configured to supply the activation signals thereto; and
a plurality of slat actuator controllers, each slat actuator controller including a plurality of independent slat actuator control channels, each slat actuator control channel (i) coupled to at least one of the electric motors that supplies the drive force to a slat actuator and (ii) configured to supply the activation signals thereto.
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Accused Products
Abstract
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.
38 Citations
20 Claims
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1. A flight control surface actuation system for aircraft having a plurality of flaps and slats on each aircraft wing, the system comprising:
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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 plurality of flap actuator controllers, each flap actuator controller including a plurality of independent flap actuator control channels, each flap actuator control channel (i) coupled to at least one of the electric motors that supplies the drive force to a flap actuator and (ii) configured to supply the activation signals thereto; and
a plurality of slat actuator controllers, each slat actuator controller including a plurality of independent slat actuator control channels, each slat actuator control channel (i) coupled to at least one of the electric motors that supplies the drive force to a slat actuator and (ii) configured to supply the activation signals thereto. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19)
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20. A flight control surface actuation system for aircraft having a plurality of flaps and slats on each aircraft wing, the system comprising:
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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 two 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 two of the electric motors, to thereby move a slat between a stowed and a deployed position; and
a plurality of flap actuator controllers, each flap actuator controller including a plurality of independent flap actuator control channels, each flap actuator control channel (i) coupled to the two electric motors that supply the drive force to the same flap actuator and (ii) configured to supply the activation signals thereto; and
a plurality of slat actuator controllers, each slat actuator controller including a plurality of independent slat actuator control channels, each slat actuator control channel (i) coupled to the two electric motors that supply the drive force to the same slat actuator and (ii) configured to supply the activation signals thereto.
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Specification