Rotor hub vibration attenuator
A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other.
1. A vibration attenuator for an aircraft, the vibration attenuator comprising:
an unbalance assembly with a base structure adapted to be mounted to a first member of the aircraft, the unbalance assembly being adapted to be rotatable about a first axis of rotation;
a first weight coupled to the base structure and adapted to be rotatable about the first axis of rotation;
a second weight coupled to the base structure and configured to be selectively positioned relative to the base structure and the first weight, the second weight selectively positioned relative to the first weight, wherein the second weight is selectively movable for changing the unbalance assembly center-of-mass relative to the first axis of rotation; and
a motor configured to rotate the unbalance assembly about the first axis of rotation at a selected speed during operation;
wherein during operation the second weight is positioned relative to the first weight so as to vary the unbalance assembly center-of-mass and create vibratory forces along the first axis of rotation for attenuation of rotor-induced vibrations having a selected frequency; and
wherein the second weight is selectively movable for changing the unbalance assembly center-of-mass relative to the first axis of rotation.
2. The vibration attenuator according to claim 1 , wherein the first weight and the second weight each have a center of mass located a selected distance from the first axis of rotation.
3. The vibration attenuator according to claim 1 , wherein the first member is coupled to at least one of a rotor hub of the aircraft and a fuselage of the aircraft.
4. The vibration attenuator according to claim 3 , wherein the first member is a rotating member of the rotor hub, the unbalance assembly is configured to rotate with the rotor hub.
5. The vibration attenuator according to claim 4 , wherein the motor is coupled to the rotating member of the rotor hub.
6. The vibration attenuator according to claim 3 , wherein the first member is a non-rotating member of the rotor hub, wherein the non-rotating member is a standpipe.
7. The vibration attenuator according to claim 6 , wherein the motor is coupled to the non-rotating member.
8. The vibration attenuator according to claim 1 , wherein during operation the rotational speed of the unbalance assembly is selectively regulated to allow attenuation of vibrations at multiple frequencies.
9. The vibration attenuator according to claim 1 , wherein the second weight rotates about the first axis of rotation.
10. The vibration attenuator according to claim 1 , wherein during operation the first weight and the second weight may be angularly positioned about the first axis of rotation relative to each other so as to produce no net force.
11. The vibration attenuator according to claim 1 , wherein during operation the first weight and the second weight may be angularly positioned about the first axis of rotation relative to each other so as to produce a maximum net force.
12. The vibration attenuator according to claim 1 , further comprising:
a clutch assembly configured to selectively position the second weight relative to the first weight.
13. The vibration attenuator according to claim 1 , wherein the second weight is selectively positioned about a second axis of rotation, the second axis of rotation being offset from the first axis of rotation, the offset generating a restoring force configured to return the second weight to a neutral position such that the unbalance assembly center-of-mass is coincident with the first axis of rotation without input from the motor.
14. The vibration attenuator according to claim 1 , wherein the motor is adapted for transferring torque to the unbalance assembly for rotating the unbalance assembly during operation.
15. The vibration attenuator according to claim 1 , wherein the first weight and the second weight are rotated in a manner that produces a selected phasing of the vibratory forces.
16. A method of attenuating vibrations in an aircraft having at least one rotor having blades, the rotor having a rotor hub configured for being driven in rotation by a mast about a mast axis of rotation, the method comprising:
(a) locating a rotatable unbalance assembly in the aircraft;
(b) rotating the unbalance assembly at a selected speed about a first rotation axis; and
(c) controlling the unbalance assembly center-of-mass position relative to the first rotation axis, and create vibratory forces along the first axis for attenuation of rotor-induced vibrations having a selected frequency.
17. The method according to claim 16 , wherein the unbalance assembly center-of-mass position is determined by the relative positions of a first weight and a second weight, wherein the second weight is selectively positioned about the first rotation axis.
18. The method according to claim 16 , wherein the unbalance assembly center-of-mass position is determined by the relative positions of a first weight and a second weight, wherein the second weight is selectively positioned about a second rotation axis, the second rotation axis being offset from the first rotation axis.
19. The method according to claim 16 , further comprising:
positioning the second weight for controlling a distance between a center of mass and the first axis of rotation.