Rotary-wing aircraft rotor having a compact articulated hub

Details Rotary-wing aircraft rotor having a compact articulated hub Rotary-wing aircraft rotor having a compact articulated hub

1980-06-04

1982-11-30

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Articulated, resiliently mounted or self-shifting impeller...

Nonmetallic resilient mounting

416140, 416141, B64C 2738

Patent

active

043614159

ABSTRACT:
The invention relates to a rotary-wing aircraft rotor.
The rotor comprises a hub 1 connected to each blade 7a by a rigid yoke 8-9 gripping the root of blade 7a and a spherical abutment 17 secured at its center C to radial arms 5a, 6a of hub 1 and bearing on its convex side against the inner end of yoke 8-9. According to the invention, an annular visco-elastic shock-absorber 20, constituting a frequency-matching device, is disposed between the yoke 8-9 associated with each blade 7a and the corresponding pitch control device 24-29.
The invention is of use inter alia in the manufacture of fast helicopter rotors having a hub which is very compact and can therefore be easily streamlined.

REFERENCES:
patent: 3111172 (1963-11-01), Gorndt et al.
patent: 3282350 (1966-11-01), Kosovec
patent: 3292712 (1966-12-01), Schmidt
patent: 3556673 (1971-01-01), Killian
patent: 3700352 (1973-10-01), Gorndt
patent: 3761199 (1973-09-01), Ferris et al.
patent: 3790302 (1974-02-01), Pascher
patent: 4135856 (1979-01-01), McGuire
patent: 4249862 (1981-02-01), Waddington et al.
patent: 4268222 (1981-05-01), Bernard
patent: 4297078 (1981-10-01), Martin

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