A rotor system includes a yoke, a plurality of blade grip assemblies and a plurality of centrifugal force bearings coupling the blade grip assemblies with the yoke. A plurality of rotor blades are coupled to the blade grip assemblies such that each rotor blade has a coincident hinge and such that each rotor blade has three independent degrees of freedom including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. A blade-to-blade damping ring includes a plurality of damper anchors each coupled to one of the blade grip assemblies along the respective pitch change axis and a plurality of lead-lag dampers each coupled between adjacent damper anchors. During blade pitch operations, each blade grip assembly is operable to rotate relative to the respective damper anchor, such that the blade-to-blade damping ring is operable to provide pitch independent lead-lag damping.
Articulated rotor systems with blade-to-blade damping
2020-03-24
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
ARTICULATED ROTOR SYSTEMS WITH BLADE-TO-BLADE DAMPING
Europäisches Patentamt | 2020
|Articulated Rotor Systems with Blade-to-Blade Damping
Europäisches Patentamt | 2019
|Structural Optimization for Light-Weight Articulated Rotor Blade
British Library Conference Proceedings | 2000
|