Device for damping the vibrations of a rotary-wing aircraft rotor
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United States of America Patent
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-
Mar 10, 1981
Grant Date -
N/A
app pub date -
Feb 5, 1979
filing date -
Feb 10, 1978
priority date (Note) -
Expired
status (Latency Note)
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Abstract
The invention relates to a device for damping the vibrations of the rotor of a rotary-wing aircraft. This device comprises a flapping weight concentrated near the rotor axis and at least three resiliently deformable elements, such as helical springs. The deformable elements are radially biassed in directions regularly distributed around the rotor axis. The inner ends of the deformable elements directly bear on the flapping weight. Their outer ends directly bear on rigid structure elements, rigidly secured to the rotor hub, so that the biassed deformable elements apply statically balanced centripetal thrusts to the flapping weight.
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