| 摘要 |
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. The helicopter vibration control system includes at least first and second nonrotating body circular force generators, the nonrotating body circular force generators fixedly coupled with the nonrotating helicopter body proximate the transmission and oriented relative to the rotating hub center Z axis, and a distributed force generation data communications network link, the distributed force generation data communications system network link linking together the nonrotating body circular force generators and the rotating hub mounted vibration control system wherein the rotating hub mounted vibration control system and the nonrotating body circular force generators are controlled to produce rotating forces wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.
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