Aircraft rotor blade with passive tuned tab

Details Aircraft rotor blade with passive tuned tab Aircraft rotor blade with passive tuned tab

1983-04-28

1985-04-30

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

With means moving working fluid deflecting working member...

416145, 416500, B64C 1300

Patent

active

045141436

ABSTRACT:
A structure (10) for reducing vibratory airloading in a rotor blade (12) with a leading edge (14) and a trailing edge (16) includes a cut-out portion (18) at the trailing edge. A substantially wedge shaped cross-section, inertially deflectable tab (20), also having a leading edge (22) and a trailing edge (24) is pivotally mounted in the cut-out portion. The trailing edge (24) of the tab (20) may move above and below the rotor blade (12). A torsion strap (26 or 64) applies force against the tab (20) when the trailing edge (24) of the tab (20) is above and below the rotor blade (12). A restraining member (92) is slidably movable along the torsion strap (64) to vary torsional biasing force supplied by the torsion bar (64) to the tab (20). A plurality of movable weights (82) positioned between plates (84) and (86) vary a center of gravity of the tab (20). Skin (74) of the tab (20) is formed from unidirectional graphite and fiberglass layers. Sliders (54 and 56), coupled with a pinned degree of freedom at rod (58) eliminate bending of tab (20) under edgewise blade deflection.

REFERENCES:
patent: 1990291 (1935-02-01), Larsen
patent: 2372030 (1945-03-01), Stalker
patent: 2405208 (1946-08-01), Harris
patent: 2514138 (1950-07-01), O'Connor
patent: 2625997 (1953-01-01), Doak
patent: 2892502 (1959-06-01), Donovan
patent: 2950768 (1960-08-01), Wagner
patent: 3215370 (1965-11-01), Strydom
patent: 3586460 (1971-06-01), Toner
patent: 3645481 (1972-02-01), Purdy
patent: 4188171 (1980-02-01), Baskin

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