Aircraft load and vibration attenuation

Patent metadata

Field	Value
Publication number	US-10647418-B2
Application number	US-201715418652-A
Country	US
Kind code	B2
Filing date	Jan 27, 2017
Priority date	May 17, 2016
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

In one embodiment, an apparatus comprises a particle damper for damping a component when the particle damper is attached to the component. The particle damper comprises a plurality of pockets configured to hold a plurality of particles, and the particle damper also comprises an attachment fitting for coupling the particle damper to the component.

First claim

What is claimed is:

1. An apparatus, comprising:
a particle damper for damping a component of an aircraft, when the particle damper is attached to the component, wherein the particle damper comprises:
a plurality of pockets configured to removably retain a plurality of particles; and
an attachment fitting for removably coupling the particle damper to an outboard end of the component.

2. The apparatus of claim 1 , wherein the particle damper is configured for attachment to a stabilizer of the aircraft to provide damping for the stabilizer.

3. The apparatus of claim 2 , wherein the stabilizer is a horizontal stabilizer.

4. The apparatus of claim 3 , wherein the horizontal stabilizer is positioned at a tail of the aircraft.

5. The apparatus of claim 2 , wherein the stabilizer is a vertical stabilizer.

6. The apparatus of claim 1 , wherein the particle damper is configured to enable adjustment of the plurality of particles contained in the plurality of pockets of the particle damper.

7. The apparatus of claim 6 , wherein the particle damper further comprises a removable cover for adjustment of the plurality of particles contained in the plurality of pockets of the particle damper.

8. The apparatus of claim 1 , wherein the plurality of pockets of the particle damper comprises at least three pockets.

9. The apparatus of claim 1 , wherein the aircraft is a rotorcraft.

10. The apparatus of claim 1 , wherein at least one pocket of the plurality of pockets comprises slideable walls for adjusting a size of the at least one pocket.

11. The apparatus of claim 1 , wherein the particle damper is integrated with a tip cap attached to the outboard end of the component.

12. The apparatus of claim 1 , wherein the plurality of particles comprises a plurality of ball bearings.

13. A rotorcraft, comprising:
a particle damper to provide damping for the rotorcraft, wherein the particle damper comprises a plurality of pockets configured to removably retain a plurality of particles and is removably coupled to an external surface of an outboard end of a component of the rotorcraft;
wherein at least one pocket of the plurality of pockets comprises slideable walls for adjusting a size of the at least one pocket.

14. The rotorcraft of claim 13 , wherein the particle damper is configured to provide damping for a stabilizer of the rotorcraft.

15. The rotorcraft of claim 14 , wherein the stabilizer is a horizontal stabilizer positioned at a tail of the rotorcraft.

16. The rotorcraft of claim 13 , wherein the particle damper is configured to enable adjustment of the plurality of particles contained in the plurality of pockets of the particle damper.

17. A method, comprising:
identifying a first configuration for a particle damper of a rotorcraft, wherein the particle damper comprises a plurality of pockets configured to removably retain a plurality of particles and an attachment fitting for removably coupling the particle damper to an external surface of an outboard end of the component;
configuring the particle damper based on the first configuration for the particle damper;
testing the particle damper to determine a performance level of the first configuration;
identifying a second configuration for the particle damper based on the performance level of the first configuration; and
configuring the particle damper based on the second configuration for the particle damper;
wherein at least one pocket of the plurality of pockets comprises slideable walls for enabling adjustment of a size of the at least one pocket.

18. The method of claim 17 , wherein identifying the second configuration for the particle damper based on the performance level of the first configuration comprises determining an adjustment to the plurality of particles used in the first configuration.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Seifert Michael S
• Howard Brett C
• Parham Jr Thomas C
• Peryea Martin Alex

Classifications

• B64C5/02

  Tailplanes · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title

• B64C2027/8281

  comprising horizontal tail planes · CPC title

• B64C27/04

  Helicopters · CPC title

• F16F7/015

  the particles being spherical, cylindrical or the like · CPC title