Self-feathering rotary wing

Details Self-feathering rotary wing Self-feathering rotary wing

1987-05-04

1988-12-06

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

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

416138, 416144, 416226, 416DIG2, 416114, B64C 2746

Patent

active

047893052

ABSTRACT:
A controllable lifting rotary wing for an aircraft wherein each rotor blade is mounted in such a manner that it has freedom to oscillate in pitch about its feathering axis. The aerodynamic center on each rotor blade is displaced forward of this feathering axis over at least a portion of the span. Cyclic aerodynamic forces on this spanwise portion cause the blade to change pitch sinusoidally once-per-revolution of the rotor whenever the rotary wing aircraft experiences a change in flight attitude or velocity. The result is that the rotor blades automatically and continuously change pitch to cancel out cyclic lateral flapping moments which are normally produced on a helicopter rotor blade by such a flight disturbance. This rotary wing has greatly improved stability by virtue of this self-feathering action. Cyclic pitch control moments are applied to the rotor blades by indirect means which do not interfere with automatic blade feathering. Means for control of collective pitch of the blades are also provided.

REFERENCES:
patent: 1692081 (1928-11-01), De La Cierva
patent: 2115754 (1938-05-01), Vaughn
patent: 2642143 (1953-06-01), Miller
patent: 2669313 (1954-02-01), Lightfoot
patent: 2754915 (1956-07-01), Echeverria
patent: 2757745 (1956-08-01), Verhage et al.
patent: 3952601 (1976-04-01), Galli et al.
patent: 4130377 (1978-12-01), Blackwell
patent: 4142837 (1979-03-01), de Simone
patent: 4514143 (1985-04-01), Campbell

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