Rotor structure, especially for rotary wing aircraft

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

1986-07-14

1987-09-01

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

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

Nonmetallic resilient mounting

416140, 416141, B64C 2735

Patent

active

046906169

ABSTRACT:
A rotor for a rotary wing aircraft has two damping structures on the outs of the blade angle adjustment sleeve. Each damping structure is a sandwich of an elastomeric layer between two stiff cover layers. A two-armed strut passes through the blade neck and is connected at its center in a pivoting manner to the blade root. The threaded outer ends of the two-armed struts pass through the respective sandwich for yieldingly connecting the radially inner end of the blade angle adjustment sleeve to the blade root. By tightening nuts on the threaded strut arms the elastomeric layer may be compressed. Thus, the damping structure performs, in addition to the damping function, a connecting function for the blade angle adjustment sleeve.

REFERENCES:
patent: 4012169 (1977-03-01), Mouille et al.
patent: 4053258 (1977-10-01), Mouille
patent: 4222709 (1980-09-01), Mouille
patent: 4244677 (1981-01-01), Noehren et al.
patent: 4252503 (1981-02-01), Wackerle et al.
patent: 4273511 (1981-06-01), Mouille et al.
patent: 4293277 (1981-10-01), Aubry
patent: 4334825 (1982-06-01), Braun et al.
patent: 4547127 (1985-10-01), Frommlet et al.

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