IN IN3822KON2009A

ROTOR HUB VIBRATION ATTENUATOR

Publication no.

IN3822KON2009A
Priority date
2007-04-24
Filing date
2009-11-04
Published
2015-10-09
Assignee
BELL HELICOPTER TEXTRON INC [US]
Inventors

RAUBER RICHARD E [US], POPELKA DAVID A [US], STAMPS FRANK B [US]

Abstract

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.

Classification

B64C27/32AI
F16C15/00AI
B06B1/164
B64C27/001
B64C27/32
F16F15/14
F16F7/1011
B64C2027/003
B64C2027/004

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