Rotor structure for a rotary wing aircraft

Details Rotor structure for a rotary wing aircraft Rotor structure for a rotary wing aircraft

1981-09-08

1984-02-21

Marcus, Stephen

Fluid reaction surfaces (i.e., impellers)

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

Nonmetallic resilient mounting

416136, 416143, 416141, B64C 2735

Patent

active

044326963

ABSTRACT:
The blade angle of the blades of a rotary wing aircraft is adjusted by a control rod (5) inside the hollow rotor head operating a control shaft (8) extending radially out of the rotor head in axial alignment with the blade angle adjustment axis. The adjustment movement of the shaft (8) is transmitted to the respective blade (3.3) by a yoke (11, 12) and a torsion-stiff sleeve (7) which bridge the blade root (3.1) and the torsion yielding blade neck (3.2) respectively. The blade root (3.1) is connected to the rotor hub (1) by a forked member (2) through which a portion (11) of the yoke extends for connection to the control shaft.

REFERENCES:
patent: Re30713 (1981-08-01), Ferris
patent: 1969077 (1934-08-01), Howe
patent: 2549886 (1951-04-01), Buivid
patent: 3261407 (1966-07-01), Culver
patent: 3310119 (1967-03-01), Watson
patent: 3926536 (1975-12-01), Ciastula et al.
patent: 4080098 (1978-03-01), Watson
patent: 4227859 (1980-10-01), Gouzien
patent: 4257738 (1981-03-01), Schwarz
patent: 4297080 (1981-10-01), Krauss

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