Aircraft rudder boost system
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United States of America Patent
Stats
-
Aug 24, 1993
Grant Date -
N/A
app pub date -
Apr 16, 1991
filing date -
Apr 16, 1991
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
The invention is a proportional rudder boost system for manually controlled aircraft which also have a yaw dampening system. The boost system includes four sensors in the pilot's and copilot's pedals including a summation means which adds the manual inputs from both pilots to provide a combined output signal to the power boost computer. Once the combined output signal exceeds a minimum force level, the boost computer signals the yaw servo to increase its torque applied to the rudder from zero in proportion to the increase in manual force applied to the rudder pedals up to a maximum power assist force level.
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