FIELD: aircraft engineering.
SUBSTANCE: invention relates to the field of aviation, in particular to rotor vibration damping device. Hover aircraft rotor (3) having hub (5) which rotates about axis (A) and has number of blades (9), drive shaft (6) connectable to drive member of aircraft (1) and connected functionally to hub (5) to rotate hub (5) about axis (A); and damping means (15) for damping vibration transmitted to shaft (6). Damping means includes include mass (17) designed to oscillate, in use, to oppose transmission to shaft (6) of vibration generated by rotation of blades (9). Mass (17) being free to slide parallel to axis (A), to oppose transmission to shaft (6) of vibration having main components along axis (A).
EFFECT: effective obstacle to transmission to the shaft of the axial oscillation is provided.
13 cl, 4 dwg
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