| 摘要 |
A rotary vane or geared rotary actuator housing is located within the interior space of a fixed aircraft wing section, forwardly of the rear spar. The actuator movable arm extends downwardly through the wing and articulates to a push rod which is pivotally connected to a movable control surface hinge fitting. A second fixed hinge fitting is connected to the rear spar, in the interior space of the fixed wing section. When the actuator operates, the arm is rotated thereby causing movement of the push rod and rotation of the control surface hinge fitting relative to the fixed hinge fitting. This results in deflection of the control surface. Location of the actuator housing forwardly of the rear spar and well forward of the hinge enables a designer to use larger and more powerful actuators since the forward end portion of the wing has greater interior volume than the hinge area. Control and power source lines are located within the wing section for protection. Further, control and power source components can be located in an area of the wing that allows integration of these components with the power hinge portion of the actuator into one line replaceable item.
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