Patent ID: 7942633

Claim:
A rotary wing aircraft rotating vibration control system for an aircraft rotary wing hub having a periodic vibration while rotating at a rotary wing aircraft operational rotation frequency about a rotary wing axis of rotation, said rotary wing aircraft rotating vibration control system comprised of: a rotary housing, said housing centered about and encompassing said rotary wing axis of rotation and rotating with said rotary wing hub at said operational rotation frequency, said housing containing a first coaxial ring motor coaxially centered about said rotary wing axis of rotation, said first coaxial ring motor having a first rotor with a first imbalance mass concentration, said housing containing a second coaxial ring motor coaxially centered about said rotary wing axis of rotation, said second coaxial ring motor having a second rotor with a second imbalance mass concentration; and an electronics control system which controls a speed and a phase of said first coaxial ring motor and a speed and a phase of said second coaxial ring motor to drive said first imbalance mass concentration and said second imbalance mass concentration wherein said rotary wing hub periodic vibration is reduced.