| 摘要 |
The invention concerns an aircraft comprising a central nacelle around which are two synchronised coaxial counter-rotating rotors each having a crown, (2, 3) and at least two blades. The nacelle comprises two interconnected structural rings (10, 11) acting as guides for the rotors. Means are provided for modifying the pitch of the blades comprising two oscillating rings (31, 32). Each oscillating ring is associated with a crown (2, 3), by being concentric thereto, and is driven in rotation by the crown, and is integral with the blades of the corresponding crown by means of connecting rods or cables. Each oscillating ring (31, 32) is secured to means for vertical displacement and displacement about a transverse axis to provide a selected distance relative to the corresponding crown (2, 3) along a circumference. The guiding of the crowns on the structural rings (10, 11) is provided by rollers (30) with perpendicular axis to the plane containing a structural ring and the corresponding crown, the rollers and the blades being equally distributed between the structural ring and the corresponding crown.
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