Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations
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United States of America Patent
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Sep 18, 2012
Grant Date -
Feb 3, 2011
app pub date -
Apr 30, 2010
filing date -
Aug 30, 2004
priority date (Note) -
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Abstract
A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub driven to rotate about a rotating hub center Z axis by a gear box transmission. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating about the rotating hub center Z axis relative to the nonrotating body, a first nonrotating body vibration sensor outputting first nonrotating body vibration sensor data correlating to vibrations.
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