| 摘要 |
An aircraft vibration control system includes an aircraft vehicle (520) having a gear box transmission (526), a nonrotating aerostructure body (524) and a rotating hub (522) driven by the transmission. A hub mounted vibration control system (HMVCS) (20) is mounted to the hub (522) with the HMVCS rotating with the hub about a rotating hub center Z-axis. The system includes a sensor (552) for outputting data correlating to rotation of the hub (522) relative to the nonrotating aerostructure body (524), and at least a first vibration sensor (554) outputting at least first vibration sensor data correlating to vibrations. The system includes first, second and third force generators (530) fixedly coupled with the aerostructure body (524) proximate the transmission (526) and oriented relative to the Z-axis, and wherein the HMVCS (20) and force generators are controlled to provide at least five degrees of freedom control and wherein the vibration sensed by the at least first nonrotating aerostructure body vibration sensor (554) is reduced. |
