| 摘要 |
A cyclic and collective pitch control device (5) for a helicopter rotor, fitted about a fixed casing (1) having an axis (A), and having a substantially sleeve-shaped movable element (12) fitted in axially-sliding manner to the casing (1); a rocking-plate assembly (6) fitted coaxially to the movable element (12) so as to rock in any direction with respect to the movable element, and in turn having an angularly-fixed first annular element (7), and a second annular element (9) rotating on the first annular element (7) together with a drive shaft (2) of the rotor fitted through the casing (1); supporting and actuating means (17) cooperating with the first annular element (7) to move the assembly (6) and the movable element (12) jointly along the axis (A) with respect to the casing (1), and to rock the assembly (6) with respect to the movable element (12); and prismatic connecting means (18, 20) between the movable element (12) and the casing (1) to prevent angular displacement of the movable element (12) with respect to the casing (1). <IMAGE>
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