A LEAD-LAG DAMPER INTEGRATED INSIDE A BLADE OF A ROTOR

A lead-lag damper arranged inside a blade of a rotor of a rotary wing aircraft. The lead-lag damper comprises an inner strength member provided with a cage in which a ball-joint connection is arranged, an outer strength member for securing to the blade, and an elastomer material member arranged betw...

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Bibliographic Details
Main Authors BERTHALON, Sylvain, BIHEL, Jean-Romain, FOURNIER, Mathias, MAZET, Stéphane
Format Patent
LanguageEnglish
French
German
Published 17.04.2019
Subjects
AEROPLANES
AIRCRAFT
AVIATION
COSMONAUTICS
HELICOPTERS
PERFORMING OPERATIONS
TRANSPORTING
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Summary:A lead-lag damper arranged inside a blade of a rotor of a rotary wing aircraft. The lead-lag damper comprises an inner strength member provided with a cage in which a ball-joint connection is arranged, an outer strength member for securing to the blade, and an elastomer material member arranged between the two strength members. The two strength members and the elastomer material member extending beyond the zone around the cage so that the relative movements between two strength members resulting from the movements of the blade are damped by deformations of the elastomer material member, at least a portion of the lead-lag damper being designed to occupy a portion of the inside of the blade that is conventionally filled with foam.
Bibliography:Application Number: EP20170194173