A rotor comprising a hub and a plurality of lift assemblies. Each lift assembly is connected to two adjacent lift assemblies respectively by a first damper and a second damper. The first damper is hinged to a lift assembly about a first axis, and the second damper is hinged to said lift assembly about a second axis. A first plane contains a lead-lag axis of the lift assembly and orthogonally to the pitch axis of the lift assembly. The first axis is situated in a volume lying between the first plane and an axis of rotation of the rotor, the second axis being positioned outside said volume.
ROTOR AND AN AIRCRAFT PROVIDED WITH SUCH A ROTOR
2018-01-04
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2019
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