The invention is related to a flexbeam unit (3) for a multiblade rotor (1) of a rotary wing aircraft, said flexbeam unit comprising a plurality of flexbeam elements (3a, 3b, 3c, 3d, 3e) that define a predetermined number of torsion elements (7a, 7b, 7c, 7d, 7e) and a ring-shaped connection zone (6) for attachment to a rotor hub (4) associated with a rotor shaft (5) of said multiblade rotor (1), each flexbeam element (3a, 3b, 3c, 3d, 3e) passing said ring-shaped connection zone (6) in a tangential manner and uninterruptedly connecting a first torsion element to a second torsion element of said predetermined number of torsion elements, wherein each flexbeam element overlaps at least one in the circumferential direction of said ring-shaped connection zone (6) immediately following flexbeam element and is overlapped by at least one in the circumferential direction of said ring-shaped connection zone (6) immediately preceding flexbeam element.
Flexbeam unit for a hingeless or a hinge- and bearingless multi-blade rotor of a rotary wing aircraft
Verwindungsträger-Einheit für einen gelenklosen oder gelenk- und lagerlosen Mehrblattrotor eines Rotorflügelluftfahrzeuges
Unité de poutre flexible pour un rotor multipale sans charnières ou sans charnières et paliers d'un véhicule aérienne à ailes rotatives
15.07.2015
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Flexbeam unit for a hingeless or a hinge and bearingless multi-blade rotor of a rotary wing aircraft
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