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US 7,607,611 B2Granted
Flight control surface actuation system with redundantly configured and lockable actuator assemblies
AssigneeHoneywell International Inc.
InventorsPaul T. Wingett, Calvin C. Potter, Casey Hanlon, Dwayne M. Benson
Life of this patent
Estimating the term…
Abstract
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.
Claims18
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 more elements
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.
2 more elements
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.
5 more elements
Dependencies are inferred from the claim text.