An aircraft rotor assembly has a yoke and a plurality of rotor blade assemblies coupled thereto. Each of the rotor blade assemblies include a rotor blade, a bearing, and a blade grip coupling the rotor blade to the bearing. Each of the rotor blades is rotatable about a lead-lag axis, flap axis, and a pitch change axis, wherein all the axes intersect within the bearing. Adjacent pairs of rotor blade assemblies are coupled together via a damper assembly that is coupled to the pitch change axis of each of the rotor blade assemblies.
Rotor Hub with Blade-to-Blade Dampers Attached to the Pitch Change Axis
04.04.2019
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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