Pitch control system for helicopter rotor blades

Details Pitch control system for helicopter rotor blades Pitch control system for helicopter rotor blades

1978-07-03

1980-04-01

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

With gyroscopic reference means for rotor control

416 31, 416 51, B64C 2772

Patent

active

041959663

ABSTRACT:
A system is disclosed for controlling the pitch angle of helicopter rotor blades to compensate for differences in lift generated by advancing and retreating blades during translational flight or due to gust loading of individual blades. Each rotor blade is free to move about its pitch axis to achieve an adjustable balance between a pitching moment exerted by the blade and centrifugal force exerted by weights rotating with the blade system. Collective and cyclic pitch commands from the pilot are transmitted through a conventional swash plate to a linkage which adjusts the relationship of the pitching-moment and centrifugal forces which produces a balanced condition. The system maintains near-constant blade lift as the blade rotates, and minimizes blade distortion and asymmetric coning, thereby significantly reducing vibration arising from a shifting of the center of mass of the rotor-blade system away from the center of rotation.

REFERENCES:
patent: 2519762 (1950-08-01), Hoffmann et al.
patent: 2614637 (1952-10-01), Landgraf
patent: 2646848 (1953-07-01), Young
patent: 2757745 (1956-08-01), Verhage et al.
patent: 2971584 (1961-02-01), Schon
patent: 3308888 (1967-03-01), Arcidiacono
patent: 3649132 (1972-03-01), Arcidiacono
patent: 4025230 (1977-05-01), Kastan

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