Active force generation system for minimizing vibration in a rotating system
A method and device for reducing vibratory noise in a system with an integral rotating member includes independently operable drive systems for controlling the angular velocity of at least two independently rotatable masses. Control signals manipulate the drive system to rotate each mass at optimal speed, direction and phase to reduce noise induced in the system by the rotating member.
1. A rotary-wing aircraft rotor system which rotates about an axis of rotation, comprising:
a rotor system having an N number of blades which rotates about an axis of rotation at a rotational speed of 1 P, such that said main rotor system produces NP vibrations;
a sensor system which senses the NP vibrations;
a multiple of masses coaxially disposed with said rotor system;
a drive system to independently spin each of said multiple of masses about said axis of rotation at an angular velocity;
a control system in communication with said sensor system and said drive system, said control system operable to identify variations of the NP vibrations to control an angular velocity of at least one of said multiple of masses to reduce the NP in-plane vibrations; and
a generator driven by said main rotor system which powers an electric motor of said drive system, each of said multiple of masses driven by an electric motor, a phase of the voltage from said generator providing a phase reference to said control system indicative of a rotational speed of said main rotor system.
2. A method of reducing vibrations in a rotary-wing aircraft main rotor system having N number of blades which rotate about an axis of rotation at a rotational speed of 1 P such that the main rotor system produces NP vibrations comprising the steps of:
(A) independently spinning a multiple of masses coaxially disposed about an axis of rotation of a main rotor system at an angular velocity greater than an angular velocity of the rotor system, each of the multiple of masses within a separate plane; and
(B) controlling an angular velocity of at least one of said multiple of masses relative to the main rotor system to reduce the NP vibrations of the main rotor system.
3. A method as recited in claim 2 , wherein said step (A) further comprises:
(a) spinning at least one of the multiple of masses in a rotational direction opposite the rotational direction of the main rotor system.
4. A method as recited in claim 2 , wherein said step (A) further comprises:
(a) spinning at least one of the multiple of masses at three additional revolution per cycle in a rotation direction of the main rotor system.
5. A method as recited in claim 2 , wherein said step (A) further comprises:
(a) spinning each of the multiple of masses continuously to continuously reduce the NP in-plane vibrations.
6. A vibration isolation system comprising:
a rotary-wing aircraft main rotor system rotatable about an axis of rotation;
a multiple of masses coaxially disposed about said axis of rotation;
a drive system interconnected to each of said multiple of masses to independently rotate each of said multiple of masses about said axis of rotation, said drive system operable to spin at least one of said multiple of masses at an angular velocity greater than an angular velocity of said rotor system, each of the multiple of masses within a separate plane; and
a control system in communication with said drive system to control the angular velocity of each of said multiple of masses to reduce in-plane vibration of said main rotor system.
7. A vibration isolation system comprising:
a rotary-wing aircraft main rotor system rotatable about an axis of rotation;
a multiple of masses coaxially disposed about said axis of rotation;
a drive system interconnected to each of said multiple of masses to independently rotate each of said multiple of masses about said axis of rotation;
a control system in communication with said drive system to control the angular velocity of each of said multiple of masses to reduce in-plane vibration of said main rotor system; and
a generator driven by said main rotor system which powers an electric motor of said drive system, each of said multiple of masses driven by an electric motor, a phase of the voltage from said generator provides a phase reference to said control system indicative of a rotational speed of said main rotor system.
8. A rotary-wing aircraft rotor system which rotates about an axis of rotation, comprising:
a rotor system having an N number of blades which rotates about an axis of rotation at a rotational speed of 1 P, such that said main rotor system produces NP vibrations;
a sensor system which senses the NP vibrations;
a multiple of masses coaxially disposed with said rotor system;
a drive system to independently spin each of said multiple of masses about said axis of rotation at an angular velocity, said drive system operable to spin at least one of said multiple of masses at an angular velocity greater than an angular velocity of said rotor system, each of the multiple of masses within a separate plane; and
a control system in communication with said sensor system and said drive system, said control system operable to identify variations of the NP vibrations to control an angular velocity of at least one of said multiple of masses to reduce the NP in-plane vibrations, wherein said multiple of masses includes a first mass which spins within a first plane and a second mass which spins within a second plane.
9. The system as recited in claim 8 , wherein said first plane is parallel to said second plane.
10. The system as recited in claim 8 , wherein said first plane is axially displaced from said second plane along said axis of rotation.
11. A rotary-wing aircraft rotor system which rotates about an axis of rotation, comprising:
a rotor system having an N number of blades which rotates about an axis of rotation at a rotational speed of 1 P, such that said main rotor system produces NP vibrations;
a sensor system which senses the NP vibrations;
a multiple of masses coaxially disposed with said rotor system;
a drive system to independently spin each of said multiple of masses about said axis of rotation at an angular velocity, said drive system operable to spin at least one of said multiple of masses at an angular velocity greater than an angular velocity of said rotor system, each of the multiple of masses within a separate plane; and
a control system in communication with said sensor system and said drive system, said control system operable to identify variations of the NP vibrations to control an angular velocity of at least one of said multiple of masses to reduce the NP in-plane vibrations, wherein each of said multiple of masses spin continuously to continuously reduce the NP in-plane vibrations.