The invention relates to a beam (13) for a rotorcraft rotor and particularly to a helicopter rotor. Said beam 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 (yy, zz) 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). According to the invention, actual offset of the hinge joint of a hingeless rotor and a bearinglesss rotor can be reduced.
Beam for a rotorcraft rotor and rotorcraft rotor
10.06.2015
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Bottom abutment device for a rotorcraft rotor, a rotorcraft rotor, and a rotorcraft
Europäisches Patentamt | 2019
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