| 摘要 |
A rudder control linkage having thermal compensation features employs a stationary thermal compensation rod, a lever with a fixed pivot, a reversing link with a movable pivot, a summing link, pilot and yaw damper input rods, and output rods. In an airplane having a fin and a rudder, the linkage is utilized to cancel undesired yaw inputs to the rudder caused by fin bending and differential thermal expansion which, if not corrected, would deleteriously affect airplane trim.
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