A rotor system (100) includes a yoke (102), a plurality of blade grip assemblies (112) and a plurality of centrifugal force bearings (122) coupling the blade grip assemblies (112) with the yoke (102). A plurality of rotor blades (104) are coupled to the blade grip assemblies (112) such that each rotor blade (104) has a coincident hinge (126) and such that each rotor blade (104) has three independent degrees of freedom including blade pitch about a pitch change axis (128), blade flap about a flapping axis (130) and lead-lag about a lead-lag axis (132). A blade-to-blade damping ring (134) includes a plurality of damper anchors (136) each coupled to one of the blade grip assemblies (112) along the respective pitch change axis (128) and a plurality of lead-lag dampers (148) each coupled between adjacent damper anchors (136). During blade pitch operations, each blade grip assembly (112) is operable to rotate relative to the respective damper anchor (136), such that the blade-to-blade damping ring (134) is operable to provide pitch independent lead-lag damping.
ARTICULATED ROTOR SYSTEMS WITH BLADE-TO-BLADE DAMPING
GELENKIGE ROTORSYSTEME MIT ROTORBLATT-ZU-BLATT DÄMPFUNG
SYSTÈMES DE ROTOR ARTICULÉS À AMORTISSEMENT INTER-PALE
2020-03-18
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Articulated rotor systems with blade-to-blade damping
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