The invention is related to a flexbeam unit (3) for a multi-blade rotor (1) of a rotary wing aircraft, said flexbeam unit (3) comprising a plurality of flexbeam elements (4) defining a predetermined number of torsion elements (5a, 5b, 5c, 5d, 5e) that are connectable with associated rotor blades (2a, 2b, 2c, 2d, 2e) of said multi-blade rotor (1), at least one of said predetermined number of torsion elements (5a, 5b, 5c, 5d, 5e) comprising at least one flexbeam element (4) having an associated longitudinal direction (4a), said at least one flexbeam element (4) comprising at least one twisted area (10) in which said at least one flexbeam element (4) is twisted in said associated longitudinal direction (4a).
Flexbeam unit with at least one twisted flexbeam element
Flexbeam-Einheit mit mindestens einem verdrilltem Flexbeam-Element
Unité à bras de flexion avec au moins un élément de flexion torsadé
2018-05-23
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Flexbeam unit with at least one twisted flexbeam element
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