Rotor hub vibration attenuator
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United States of America Patent
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Apr 23, 2013
Grant Date -
Aug 19, 2010
app pub date -
Apr 24, 2007
filing date -
Apr 24, 2007
priority date (Note) -
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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.
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