Aircraft control surface drive mechanism
AssigneeNabtesco Corporation
InventorKoji Ito
Life of this patent
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Abstract
An actuator includes a plurality of cylinder units each including a cylinder and a rod, and is pivotably attached, at a first end thereof, to a control surface. A reaction link is pivotably attached, at a first end thereof, to a fulcrum shaft rotatably supporting the control surface. The reaction link is pivotably attached, at a second end thereof, to a second end of the actuator between the plurality of cylinder units.
Claims6
An aircraft control surface drive mechanism that is provided as a link mechanism comprising a hydraulically operated actuator and a reaction link connected to the actuator, and that drives a control surface of an aircraft,
- wherein the actuator includes a plurality of cylinder units each including a cylinder and a rod, and is pivotably attached, at a first end thereof, to the control surface or a control surface-side member attached to the control surface, and
- the reaction link is pivotably attached, at a first end thereof, to a fulcrum shaft rotatably supporting the control surface, and is pivotably attached, at a second end thereof, to a second end of the actuator between the plurality of cylinder units.
Dependencies are inferred from the claim text.