| 摘要 |
The helicopter rotor blades (4) rotate about an axis (A-A) on a hub (3) on the rotor mast (2) and about a longitudinal pitch change axis (X-X). The pitch lever (5) is controlled by a pitch rod (6) pivoted on a plate (8), rotating with the mast, belonging to a cyclical plate mechanism (7). The plate rotates on a non rotating plate (11) able to slide axially (13) along the mast and incline (12) in all directions relative to the mast, under the action of the flight control activator (15). Each blade has a connector (16) pivoted to two levers (17,18) pivoted one on the other through a first point (19). The first lever (17) is pivoted by the others in a second reference point (20) rotating with the hub. The second lever (18) is pivoted through a third point (21) on the pitch lever. The pitch rod (6) pivots on one of the levers in a point distinct from its pivot on the rotating plate to angularly move the levers for optimum pitch control.
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