Helicopter vibration control system and rotating assembly rotary forces generators for canceling vibrations

A rotating vibration control system for a rotating assembly having at least a first vibration frequency operational vibration and at least a second vibration frequency operational vibration, said rotating vibration control system comprised of:

• a first rotor with a first imbalance mass concentration, said first rotor driven to rotate at a first rotation speed greater than an operational rotation frequency of said rotating assembly,
• a second rotor with a second imbalance mass concentration, said second rotor driven to rotate at said first rotation speed greater than an operational rotation frequency of said rotating assembly
• a third rotor with a third imbalance mass concentration, said third rotor driven to rotate at a second rotation speed greater than an operational rotation frequency of said rotating assembly
• a fourth rotor with a fourth imbalance mass concentration, said fourth rotor driven to rotate at said second rotation speed greater than an operational rotation frequency of said rotating assembly
• at least a first vibration sensor for producing a plurality of first vibration sensor signals,
• at least a second vibration sensor for producing a plurality of second vibration sensor signals,
• a first rotor rotational position sensor,
• a second rotor rotational position sensor,
• a third rotor rotational position sensor,
• a fourth rotor rotational position sensor,
• a first motor control loop for controlling the rotation of said first rotor and the rotation of said second rotor,
• a first vibration control loop for providing commands to the first motor control loop to minimize said first vibration sensor signals and said second vibration sensor signals,
• a second motor control loop for controlling the rotation of said third rotor and the rotation of said fourth rotor,
• a second vibration control loop for providing commands to the second motor control loop to minimize said first vibration sensor signals and said second vibration sensor signals.

A rotary wing aircraft rotating hub mounted vibration control system for a rotary wing hub having at least a first and a second vibration frequency while rotating at a rotary wing operational rotation frequency, said rotating hub mounted vibration control system comprised of:

• a system housing, said system housing attached to said rotary wing hub and rotating with said rotary wing hub at said operational rotation frequency, said housing a first coaxial ring motor having a first rotor with a first imbalance mass concentration, a second coaxial ring motor having a second rotor with a second imbalance mass concentration,
• a third coaxial ring motor having a third rotor with a third imbalance mass concentration, a fourth coaxial ring motor having a fourth rotor with a fourth imbalance mass concentration,
• an electronics control system for controlling the vibration control system
• said electronics control system including a first rotation speed rotor stage VC controller electronics control subsystem for controlling a rotational position of said first imbalance mass concentration rotor and a rotational position of said second imbalance mass concentration rotor, said first rotation speed rotor stage VC controller electronics control subsystem controlling a speed and a phase of said first coaxial ring motor and said second coaxial ring motor such that said first imbalance mass concentration and said second imbalance mass concentration are driven at a whole number multiple vibration canceling rotation frequency greater than said operational rotation frequency wherein said first rotary wing hub vibration frequency is reduced, said electronics control system including a second rotation speed rotor stage VC controller electronics control subsystem for controlling a rotational position of said third imbalance mass concentration rotor and a rotational position of said fourth imbalance mass concentration rotor, said second rotation speed rotor stage VC controller electronics control subsystem controlling a speed and a phase of said third coaxial ring motor and said fourth coaxial ring motor such that said third imbalance mass concentration and said fourth imbalance mass concentration are driven at a whole number multiple vibration canceling rotation frequency greater than said operational rotation frequency wherein said second helicopter rotary wing hub vibration frequency is reduced.

A method of controlling a plurality of vibration frequencies of an aircraft with a rotary hub which rotates at an operational rotation frequency, said method including

• providing an annular ring housing containing a first coaxial ring motor having a first rotor with a first imbalance mass concentration, a second coaxial ring motor having a second rotor with a second imbalance mass concentration, a third coaxial ring motor having a third rotor with a third imbalance mass concentration, a fourth coaxial ring motor having a fourth rotor with a fourth imbalance mass concentration, and an electronics control system for controlling the vibration control system said electronics control system including a first rotation speed rotor stage VC controller electronics control subsystem for controlling a rotational position of said first imbalance mass concentration rotor and a rotational position of said second imbalance mass concentration rotor, said electronics control system including a second rotation speed rotor stage VC controller electronics control subsystem for controlling a rotational position of said third imbalance mass concentration rotor and a rotational position of said fourth imbalance mass concentration rotor, and
• securing said annular ring housing to said rotary hub with said annular ring housing rotating at said operational rotation frequency with said rotary hub, driving said first rotor and said second rotor at a first whole number multiple vibration canceling rotation frequency greater than said operational rotation frequency while controlling the rotational position of said first imbalance mass concentration and said second imbalance mass concentration in order to inhibit a first vibration frequency driving said third rotor and said fourth rotor at a second whole number multiple vibration canceling rotation frequency greater than said operational rotation frequency while controlling the rotational position of said third imbalance mass concentration and said fourth imbalance mass concentration in order to inhibit a second vibration frequency.