Twist control for helicopter tail rotor pitch change

Details Twist control for helicopter tail rotor pitch change Twist control for helicopter tail rotor pitch change

1979-04-24

1982-09-14

Jillions, John M.

Fluid reaction surfaces (i.e., impellers)

Sustained ancillary movement of rotary working member

Lead-lag type rotor blade movement

416134A, 416141, B64C 2738

Patent

active

043493165

ABSTRACT:
A control for a helicopter tail rotor where inboard twist sections on opposite sides of a central hub section are adjacent to pitch horns mounted outboard the margins of the twist sections and extend to a negative delta.sub.3 connection point located at the virtual bending axis of each twist section. The rotor teeters on the tail mast with the span axis of the rotor at an angle of the order of 30.degree. to 45.degree. from the teetering axis.

REFERENCES:
patent: 2627929 (1953-02-01), Sikorsky
patent: 2934152 (1960-04-01), Dauenhauer
patent: 3026942 (1962-03-01), Cresap
patent: 3193019 (1965-07-01), Drees et al.
patent: 3347320 (1967-10-01), Cresap et al.
patent: 3457997 (1969-07-01), Mackenzie et al.
patent: 3484174 (1969-12-01), McCoubrey
patent: 3494706 (1970-02-01), Gaffey et al.
patent: 3765267 (1973-10-01), Bourquardez et al.
patent: 3790302 (1974-02-01), Pascher
patent: 3874820 (1975-04-01), Fenaughty
patent: 4037988 (1977-07-01), Laird

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