Rotor hub vibration attenuator

Patent metadata

Field	Value
Publication number	US-11148790-B2
Application number	US-202016794075-A
Country	US
Kind code	B2
Filing date	Feb 18, 2020
Priority date	Mar 14, 2016
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

First claim

What is claimed is:

1. A vibration isolation system for a rotary-wing aircraft main rotor system having a mast that is rotatable about an axis of rotation, the vibration isolation system comprising:
a first mass attached to the mast and rotatable relative to the mast coaxially about said axis of rotation;
a second mass attached to the mast and rotatable relative to the mast and the first mass coaxially about said axis of rotation; and
an intermediate plate rotatable about said axis of rotation and coupling the first and second masses, the intermediate plate comprising guide slots;
wherein the second mass is mechanically linked to the first mass through the guide slots of the intermediate plate, and
wherein the angular velocity of the first and second masses is operable to reduce in-plane vibration of said main rotor system.

2. The system of claim 1 , wherein the first mass includes a first weight assembly having a first extension portion extending in a radial direction from the mast towards a distal end of the first weight assembly, and
wherein the second mass includes a second weight assembly having a second extension portion extending in a radial direction from the mast towards a distal end of the second weight assembly.

3. The system of claim 2 , wherein each of the first and second weight assemblies comprises an armature for coupling the associated weight to one of the guide slots.

4. The system of claim 1 , wherein each of the first and second weight assemblies includes a respective spring for tuning the system to a target frequency.

5. The system of claim 1 , wherein each guide slot defines an arc-shaped path.

6. An aircraft comprising:
a rotary-wing aircraft main rotor system having a mast that is rotatable about an axis of rotation;
a vibration isolation system comprising:
a first mass attached to the mast and rotatable relative to the mast coaxially about said axis of rotation;
a second mass attached to the mast and rotatable relative to the mast and the first mass coaxially about said axis of rotation; and
an intermediate plate rotatable about said axis of rotation and coupling the first and second masses, the intermediate plate comprising guide slots;

wherein the second mass is mechanically linked to the first mass through the guide slots of the intermediate plate, and
wherein the angular velocity of the first and second masses is operable to reduce in-plane vibration of said main rotor system.

7. The aircraft of claim 6 , wherein the first mass includes a first weight assembly having a first extension portion extending in a radial direction from the mast towards a distal end of the first weight assembly, and
wherein the second mass includes a second weight assembly having a second extension portion extending in a radial direction from the mast towards a distal end of the second weight assembly.

8. The aircraft of claim 7 , wherein each of the first and second weight assemblies comprises an armature for coupling the associated weight to one of the guide slots.

9. The system of claim 6 , wherein each of the first and second weight assemblies includes a respective spring for tuning the system to a target frequency.

10. The aircraft of claim 6 , wherein each guide slot defines an arc-shaped path.

Assignees

• Textron Innovations Inc

Inventors

• Choi Jouyoung Jason
• Heverly David
• Seifert Michael
• Smith Michael
• Stamps Frank
• Parham Jr Thomas
• Kizhakkepat Amarjit Olenchery

Classifications

• B64C27/001 Primary

  Vibration damping devices · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C2027/003

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