Bearingless hub structure for rotary-wing aircrafts

Fluid reaction surfaces (i.e. – impellers) – Articulated – resiliently mounted or self-shifting impeller... – Nonmetallic resilient mounting

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416141, B64C 2738

Patent

active

046767207

ABSTRACT:
A bearingless hub structure for rotary-wing aircrafts comprising a hub body ecured to a rotor shaft, a plurality of radially extending flexbeams integrally formed with the hub body, and pitch housings enclosing each of the flexbeams in spaced relationship, the pitch housing having a radially outer end portion rigidly secured to an inboard end of a rotor blade and a radially inner end portion supported by a spherical bearing in the vicinity of a root end of said flexbeam.
The flexbeam consists of a flexible element of low lead-lag stiffness and a torsion element of low torsional stiffness located radially outside the flexible element. The flexible element consists of two beam-like members having radially inner ends spaced in the lead-lag direction and extending radially outward with narrowing the distance between them, the beam-like member having radially outer end connected to a radially inner end of the torsion element.

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patent: 4292009 (1981-09-01), Weiland et al.
patent: 4299538 (1981-11-01), Ferris et al.
patent: 4427340 (1984-01-01), Metzger et al.
patent: 4516909 (1985-05-01), Caramaschi et al.

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