| 摘要 |
The invention relates to a vibration damper, in particular for a helicopter rotor, the damper comprising both a driving element (10) and a rigid element (6) and including a damper assembly functionally interconnecting the driving element (10) and the rigid element (6), the damper assembly comprising firstly a hydraulic damper device disposed in at least one viscous fluid cavity (3) and a laminated flexible device (1). The hydraulic damper device (40, 50) comprises first and second sets (40, 50) of interleaved plane vanes. In the invention, the hydraulic damper device also has at least one damper element which is disposed in one of said viscous fluid cavities and which is secured to the driving element (10), said damper element presenting an outer outline which tapers going away from a base (23) situated beside one axial end of the damper towards an apex situated beside the sets (40, 50) of plane vanes.
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