Rotorcraft rotor with blades hinged in flap and in lag

Details Rotorcraft rotor with blades hinged in flap and in lag Rotorcraft rotor with blades hinged in flap and in lag

2006-09-20

2009-10-27

Kershteyn, Igor (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Sustained ancillary movement of rotary working member

Lead-lag type rotor blade movement

C416S107000, C416S140000, C416S141000, C416S143000

Reexamination Certificate

active

07607892

ABSTRACT:
The invention relates to a rotorcraft rotor comprising a hub and at least two blades hinged relative to the hub about respective pitch axes and about respective flap axes, and about respective lag axes; each blade is secured to a respective pitch lever; the rotor includes a respective pitch control rod connected to each pitch lever by a first ball joint, and a common lag damper system centered substantially on the axis of rotation of the rotor and connected to each of the blades; the damper system is secured to a respective lateral projection from each blade via a respective second ball joint that is sufficiently close to the first ball joint connecting the pitch rod to the pitch lever for the lag damper system to be relatively insensitive to flap oscillations of the hinged blades.

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