Vibration attenuator

Patent metadata

Field	Value
Publication number	US-11724800-B2
Application number	US-202217567874-A
Country	US
Kind code	B2
Filing date	Jan 3, 2022
Priority date	Nov 21, 2018
Publication date	Aug 15, 2023
Grant date	Aug 15, 2023

Abstract

A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.

First claim

What is claimed is:

1. A vibration attenuator for an aircraft having a rotor rotatable about a mast axis, the attenuator comprising:
upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis, the weight assemblies being configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis; and
a first motor configured for selective translation of one of the weight assemblies relative to the other of the weight assemblies along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.

2. The vibration attenuator of claim 1 , wherein the weight of each weight assembly is coupled to an arm extending radially from a central portion of the associated weight assembly.

3. The vibration attenuator of claim 1 , further comprising:
a second motor for causing rotation of the weight assemblies relative to the rotor.

4. The vibration attenuator of claim 1 , wherein the first motor is a linear motor.

5. The vibration attenuator of claim 1 , wherein the first motor is a rotary motor.

6. A vibration attenuator for an aircraft having a rotor rotating about a mast axis, the attenuator comprising:
an upper weight assembly comprising an arm and an upper weight, the center of gravity of the upper weight being a radial distance from the mast axis;
a lower weight assembly comprising an arm and a lower weight, the center of gravity of the lower weight being the radial distance from the mast axis; and
a first motor configured for selectively translating one weight assembly relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes;
wherein the upper and lower weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis.

7. The vibration attenuator of claim 6 , further comprising:
a second motor for causing rotation of the weight assemblies relative to the rotor.

8. The vibration attenuator of claim 6 , wherein the first motor is a linear motor.

9. The vibration attenuator of claim 6 , wherein the first motor is a rotary motor.

10. An aircraft, comprising:
at least one rotor rotatable about a mast axis;
a vibration attenuator, comprising:
upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis, the weight assemblies being configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis; and
a first motor configured for selective translation of one of the weight assemblies relative to the other of the weight assemblies along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.

11. The aircraft of claim 10 , wherein the weight of each weight assembly is coupled to an arm extending radially from a central portion of the associated weight assembly.

12. The aircraft of claim 10 , further comprising:
a second motor for causing rotation of the weight assemblies relative to the rotor.

13. The aircraft of claim 10 , wherein the first motor is a linear motor.

14. The aircraft of claim 10 , wherein the first motor is a rotary motor.

Assignees

• Textron Innovations Inc

Inventors

• Stamps Frank Bradley
• Heverly David
• Smith Michael R
• Seifert Michael Scott
• Parham Jr Thomas C
• Miller Gary
• Choi Jouyoung Jason
• Rauber Richard E

Classifications

• B64C27/001 Primary

  Vibration damping devices · CPC title

• B64C2027/003

  mounted on rotor hub, e.g. a rotary force generator · CPC title

• B64C2027/005

  using suspended masses · CPC title

• F16F15/20 Primary

  Suppression of vibrations of rotating systems by favourable grouping or relative arrangements of the moving members of the system or systems {(F16F15/24 takes precedence)} · CPC title

• F16F15/22

  Compensation of inertia forces {(suppression of vibrations of rotating systems by favourable grouping or relative arrangements of the moving members of the system or systems F16F15/20, counterweights F16F15/28; correcting-weights for balancing rotating bodies F16F15/32)} · CPC title