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
2020-09-15
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Rotor Hub with Blade-to-Blade Dampers Attached to the Pitch Change Axis
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