A rotor damping system includes a rotor blade defining opposed leading and trailing edges, wherein the rotor blade has flexibility in an edgewise direction defined between the leading and trailing edges. A spar is mounted within the rotor blade, wherein the spar is stiff against flexure in the edgewise direction. A damper is operatively connected to the spar for damping relative motion of the spar and blade.
ROTOR DAMPING
06.07.2017
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |