| 摘要 |
There is described a rotor (1) for a helicopter, having a hub (2) rotating about a first axis (A); a number of blades (3) projecting from the hub (2) in respective longitudinal directions (C) lying in a plane crosswise to the first axis (A), and each connected to the hub (2) so as to be movable at least about a second axis (B) crosswise to the first axis (A) and to the relative longitudinal direction (C); and a number of damping devices (4) for damping vibration of the helicopter, and each interposed between a respective blade (3) and the hub (2); each damping device (4) has a plate member (20) fixed, on one side, to the hub (2), connected, on the opposite side, to the relative blade (3) by elastic means (28, 29), and flexible, during movement of the blade (3), about a third axis (D) coaxial with the second axis (B).
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