Vibration attenuator

Patent metadata

Field	Value
Publication number	US-11577825-B2
Application number	US-202016862257-A
Country	US
Kind code	B2
Filing date	Apr 29, 2020
Priority date	Oct 25, 2018
Publication date	Feb 14, 2023
Grant date	Feb 14, 2023

Abstract

A vibration attenuator for a rotor of an aircraft has a housing adapted for rotation with the rotor about an axis. A first ring is rotatably carried within the housing on a first bearing, a first weight being coupled to the first ring for rotation therewith relative to the housing about the axis. A second ring is rotatably carried by the first ring on a second bearing, a second weight being coupled to the second ring for rotation therewith relative to the housing and to the first ring. A first motor is configured for rotating the first ring relative to the housing, and a second motor is configured for rotating the second ring relative to the housing and to the first ring. The first and second motors are operated to rotate the weights within the housing and position the weights relative to each other for attenuating vibrations.

First claim

What is claimed is:

1. A vibration attenuator for a rotor of an aircraft, the attenuator comprising:
a housing adapted for rotation with the rotor about an axis;
a first ring rotatably carried within the housing on a first bearing, a first weight being coupled to the first ring for rotation therewith relative to the housing about the axis;
a second ring rotatably carried by the first ring on a second bearing, a second weight being coupled to the second ring for rotation therewith relative to the housing and to the first ring;
a stop member located on the first ring and configured for abutting a corresponding feature of the second ring for limiting the relative rotation of the rings between positions corresponding to a minimum-force configuration, in which the weights are positioned 180 degrees apart;
a first motor configured for rotating the first ring relative to the housing; and
a second motor configured for rotating the second ring relative to the housing and to the first ring;
wherein the first and second motors are operated to rotate the weights within the housing and position the weights relative to each other for attenuating vibrations.

2. The attenuator of claim 1 , wherein each motor is a linear motor.

3. The attenuator of claim 1 , wherein each motor is an interrupted linear motor.

4. The attenuator of claim 1 , wherein each motor is located radially inboard of the associated ring.

5. The attenuator of claim 1 , wherein the rings are in a stacked configuration.

6. The attenuator of claim 1 , wherein each bearing is located radially outboard of the associated ring.

7. The attenuator of claim 1 , wherein an inner race of each bearing is coupled to the associated ring, an outer race of the first bearing is coupled to the housing, and an outer race of the second bearing is coupled to the first ring.

8. The attenuator of claim 1 , wherein during startup using the motor of one of the rings, inertia of the other of the rings causes the weights to be positioned in the minimum-force configuration.

9. The attenuator of claim 1 , wherein during shutdown using the motor of one of the rings, momentum of the other of the rings causes the weights to be positioned in the minimum-force configuration.

10. The attenuator of claim 1 , wherein the attenuator is adapted for pivoting together with the rotor during flapping of the rotor.

11. A vibration attenuator for a rotor of an aircraft, the attenuator comprising:
a housing adapted for rotation with the rotor about an axis;
a lower weight coupled to a lower ring rotatably carried by a housing for rotation about the axis;
an upper weight coupled to an upper ring rotatably carried by the lower ring for rotation about the axis;
a stop member located on one of the rings and configured for abutting a corresponding feature of the other ring for limiting the relative rotation of the rings between positions corresponding to a minimum-force configuration, in which the weights are positioned 180 degrees apart;
a first motor configured for rotating the first ring relative to the housing; and
a second motor configured for rotating the second ring relative to the housing and to the first ring;
wherein the first and second motors are operated to rotate the weights within the housing and position the weights relative to each other for attenuating vibrations.

12. The attenuator of claim 11 , wherein each motor is a linear motor.

13. The attenuator of claim 11 , wherein each motor is an interrupted linear motor.

14. The attenuator of claim 11 , wherein each motor is located radially inboard of the associated ring.

15. The attenuator of claim 11 , wherein the rings are in a stacked configuration.

16. The attenuator of claim 11 , wherein each bearing is located radially outboard of the associated ring.

17. An aircraft having a rotor, the rotor comprising:
a hub;
a plurality of blades coupled to the hub;
a vibration attenuator, comprising:
a housing coupled to the hub for rotation with the rotor about an axis;
a first ring rotatably carried within the housing on a first bearing, a first weight being coupled to the first ring for rotation therewith relative to the housing about the axis;
a second ring rotatably carried by the first ring on a second bearing, a second weight being coupled to the second ring for rotation therewith relative to the housing and to the first ring;
a stop member located on the first ring and configured for abutting a corresponding feature of the second ring for limiting the relative rotation of the rings between positions corresponding to a minimum-force configuration, in which the weights are positioned 180 degrees apart;
a first motor configured for rotating the first ring relative to the housing; and
a second motor configured for rotating the second ring relative to the housing and to the first ring;

wherein the first and second motors are operated to rotate the weights within the housing and position the weights relative to each other for attenuating vibrations.

Assignees

• Bell Textron Inc
• Textron Innovations Inc

Inventors

• Stamps Frank Bradley
• Heverly David

Classifications

• F16F15/1485

  the rotation being unlimited with respect to driving means (with a fluid connection between inertia member and rotating driving means F16F15/167) · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• F16F2222/08

  Inertia · CPC title

• F16F2232/02

  Rotary · CPC title

• H02K7/14

  Structural association with mechanical loads, e.g. with hand-held machine tools or fans (with fan or impeller for cooling the machine H02K9/06) · CPC title