The invention relates to a beam (13) for a rotorcraft rotor and particularly to a helicopter rotor. Said beam (13) comprises a hub connection portion (14), a blade connection portion (15), a first flexure portion (16) located between the hub connection portion (14) and the blade connection portion (15) and having a bending stiffness about a first axis which is orthogonal to the longitudinal axis (X) of the blade (12), said bending stiffness being smaller than that of the hub connection portion (14) and that of the blade connection portion (15) and a shear portion (17) located between the hub connection portion (14) and the blade connection portion (15) and having a shear stiffness parallel to a second axis which is orthogonal to the longitudinal axis (X) of the blade (12) and non-parallel to the first axis. Said shear stiffness is smaller than that of the hub connection portion (14) and that of the blade connection portion (15).
Beam for a rotorcraft rotor and rotorcraft rotor
Träger für einen Drehflüglerrotor und Drehflüglerrotor
Poutre pour un rotor de giravion et ledit rotor
2015-06-17
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Bottom abutment device for a rotorcraft rotor, a rotorcraft rotor, and a rotorcraft
European Patent Office | 2019
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