Articulated rotor for helicopters

Fluid reaction surfaces (i.e. – impellers) – Articulated – resiliently mounted or self-shifting impeller... – Including movement limit stop or damping means

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Details

416107, 416141, B64C 2738

Patent

active

043425402

ABSTRACT:
The multi-blade articulated rotor for helicopters, comprises a hub connected to a shaft rotatable substantially about a vertical axis, the hub being in the form of a plate comprising a plurality of perforations, each of which defines a bridge of material of said plate between a part of the edge of said perforation and a part of the edge of said plate; a plurality of yokes, each of which is substantially of U shape and comprises a pair of substantially parallel arms and a base element which connects together one end of said arms, the other end of the arms being connected to one of said blades, said base element being inserted into one of said perforations in the hub; a plurality of elastomer bearings, each of which is disposed between said base element of a yoke and the corresponding hub bridge; and means for limiting the amplitude of the swivel movement which each of said yokes can make substantially in a vertical plane.

REFERENCES:
patent: 3147810 (1964-09-01), Mosinskis
patent: 3282350 (1966-11-01), Kisovec
patent: 3762834 (1973-10-01), Bourquardez
patent: 3932059 (1976-01-01), Rybicki
patent: 3967918 (1976-07-01), Mouille et al.
patent: 4012169 (1977-03-01), Mouille et at.
patent: 4105365 (1978-08-01), Ferris et al.
patent: 4178130 (1979-12-01), Ferris et al.
patent: 4203708 (1980-05-01), Rybicki
patent: 4235570 (1980-11-01), Ferris et al.
patent: 4257739 (1981-03-01), Covington et al.
patent: 4304525 (1981-12-01), Mouille

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