Helicopter rotors

Fluid reaction surfaces (i.e. – impellers) – Articulated – resiliently mounted or self-shifting impeller... – Resilient bias or mount

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416141, B64C 2738

Patent

active

044962843

ABSTRACT:
Diametrically opposed rotor blades of a helicopter rotor are interconnected by a strap member which is flexible in torsion and in a plane perpendicular to a plane of rotation and has a plan profile extending between leading and trailing edges. Each rotor blade is provided with inwardly extending lever means adapted for attachment to drive means externally of the strap plan profile and adjacent one of its edges and to pitch control means externally of the plan profile and adjacent the other of its edges. In one embodiment, the lever means comprise individual levers formed integral with a connecting member rotationally fixed to the rotor blade and in a further embodiment the lever means comprise an inwardly extending torque sleeve. The drive means attachments of opposed blades lie along a common axis parallel to the plane of rotation and intersecting the axis of rotation at approximately 45 degrees to a longitudinal axis of the strap member.

REFERENCES:
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patent: 4093400 (1978-06-01), Rybicki
patent: 4163630 (1979-08-01), Weiland
patent: 4182597 (1980-01-01), Derschmidt
patent: 4227857 (1980-10-01), Reyes
patent: 4281966 (1981-08-01), Duret et al.
patent: 4299538 (1981-11-01), Ferris et al.
patent: 4307996 (1981-12-01), Watson
patent: 4332525 (1982-06-01), Cheney
patent: 4340335 (1982-07-01), Cheney
patent: 4369018 (1983-01-01), Brunsch et al.

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