Damping device for a helicopter rotor blade

Details Damping device for a helicopter rotor blade Damping device for a helicopter rotor blade

1980-08-04

1982-11-23

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

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

Plural articulation

416134A, 416138, B64C 2735

Patent

active

043603378

ABSTRACT:
The wing blades of a helicopter rotor each are connected to the rotor hub a connection, e.g. a spar being .fwdarw..rarw. including a hinge which is at least fictitious to permit lead-lag movements of the blades <yielding relative to torsion to permit the blade angle adjustment>. A rod, which is stiff in the lead-lag direction and yielding against torsion, is connected in parallel to the connection between the blade root and the rotor hub. One connection of the rod is rigid, for example the connection to the blade root. The other connection of the rod is elastically yielding substantially only in the plane of the rotor whereby a substantial damping of blade movements in the lead-lag direction is accomplished.

REFERENCES:
patent: 3879153 (1975-04-01), Breuner
patent: 3880551 (1975-04-01), Kisorec
patent: 4008980 (1977-02-01), Noehren et al.
patent: 4111605 (1978-09-01), Roman et al.
patent: 4201515 (1980-05-01), Derschmidt et al.
patent: 4266912 (1981-05-01), Roman

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