Rotor structure, especially for a rotary wing aircraft

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

1987-09-29

1988-10-18

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

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

Nonmetallic resilient mounting

416140, 416141, 416138, B64C 2735

Patent

active

047783435

ABSTRACT:
In order to avoid a negative coupling between blade lead-lag movements and lade angle adjustment movements in a helicopter rotor, the angle (.beta.) between a control rod (5) for the blade angle adjustment and an effective damping plane (M) of the rotor is increased as compared to the respective angle in conventional rotors. This increase of the angle (.beta.) is accomplished by arranging a damping device (9) having the effective plane (M) for suppressing blade lead-lag movements in such a way on a blade angle control sleeve (4), that the effective plane (M) of the damping device (9) encloses an angle (.alpha.) with the lead-lag plane of the rotor.

REFERENCES:
patent: 4087203 (1978-05-01), Ferris
patent: 4332525 (1982-06-01), Cheney
patent: 4381902 (1983-05-01), Head et al.
patent: 4427340 (1984-01-01), Metzger et al.
patent: 4547127 (1985-10-01), Frommlet et al.
patent: 4592701 (1986-06-01), Hahn et al.
patent: 4676720 (1987-06-01), Niwa et al.
patent: 4690615 (1987-09-01), Kuntze-Fechner et al.
patent: 4690616 (1987-09-01), Hahn et al.

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