Rotor structure for a rotary wing aircraft

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

1980-01-21

1982-08-24

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

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

Nonmetallic resilient mounting

416141, 416230, B64C 2738

Patent

active

043458769

ABSTRACT:
The wings of a rotary wing aircraft comprise, for example, four wing blades orming two pairs of wing blades whereby the blades of a pair are located diametrically opposite each other. The blades of a pair are connected to each other by a spar extending from wing blade to wing blade. The spar is operatively secured to the rotor head. Each spar has between the rotor head and the respective wing blade a zone with a torsion yieldability larger than in the spar outside said zone. A beam stiff against bending, bridges the zone, referred to as a torque soft zone, from the wing blade toward the rotor head except for a small flexible section between the rotor head and the radially inner end of the beam. The flexible section permits the blade flapping movements and the blade lead-lag movements.

REFERENCES:
patent: 3261407 (1966-07-01), Culver et al.
patent: 3885887 (1975-05-01), Desjardins
patent: 3999887 (1976-12-01), McGuire
patent: 4053258 (1977-10-01), Mouille
patent: 4087203 (1978-05-01), Ferris
patent: 4222709 (1980-09-01), Mouille
patent: 4227859 (1980-10-01), Gouzien et al.
patent: 4244677 (1981-01-01), Noehren et al.

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