Helicopter vibration control system and rotary force generator for canceling vibrations

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 rotor coaxially centered about said rotary wing axis of rotation, said first rotor having a first imbalance mass concentration, said housing containing a second rotor coaxially centered about said rotary wing axis of rotation, said second rotor having a second imbalance mass concentration;
• a health monitoring sensor for monitoring a change in an operational characteristic of said vibration control system,
• and
• an electronics control system which controls a first rotor drive means to drive said first rotor with a first rotor speed and phase and controls a second rotor drive means to drive said second rotor with a second rotor speed and phase to drive
• said first imbalance mass concentration and said second imbalance mass concentration to reduce said rotary wing hub periodic vibration.

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 rotor coaxially centered about said rotary wing axis of rotation, said first rotor having a first imbalance mass concentration, said housing containing a second rotor coaxially centered about said rotary wing axis of rotation, said second rotor having a second imbalance mass concentration;
• and
• an electronics control system which controls a first rotor drive means to drive said first rotor with a first rotor speed and phase and controls a second rotor drive means to drive said second rotor with a second rotor speed and phase to drive
• said first imbalance mass concentration and said second imbalance mass concentration to reduce said rotary wing hub periodic vibration, with said electronics control system controlling a means for braking a rotation of said imbalance mass concentrations.

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 rotor coaxially centered about said rotary wing axis of rotation, said first rotor having a first imbalance mass concentration, said housing containing a second rotor coaxially centered about said rotary wing axis of rotation, said second rotor having a second imbalance mass concentration;
• and
• an electronics control system which controls a first rotor drive means to drive said first rotor with a first rotor speed and phase and controls a second rotor drive means to drive said second rotor with a second rotor speed and phase to drive
• said first imbalance mass concentration and said second imbalance mass concentration to reduce said rotary wing hub periodic vibration, with said electronics control system opposingly orienting said first imbalance mass concentration and said second imbalance mass concentration at a transitioning rotation speed.