US 11,987,347 B2
Single-blade aircraft rotor
Jean-Michel Simon, Chatillon (FR); and Louis Chemouni, Verneuil-sur-Seine (FR)
Assigned to INNOSTAR, Chatillon (FR); and HUTCHINSON, Paris (FR)
Appl. No. 17/774,285
Filed by INNOSTAR, Chatillon (FR); and HUTCHINSON, Paris (FR)
PCT Filed Nov. 4, 2020, PCT No. PCT/EP2020/080951
§ 371(c)(1), (2) Date May 4, 2022,
PCT Pub. No. WO2021/089616, PCT Pub. Date May 14, 2021.
Claims priority of application No. 1912342 (FR), filed on Nov. 4, 2019.
Prior Publication US 2022/0388641 A1, Dec. 8, 2022
Int. Cl. B64C 27/473 (2006.01); B64C 27/00 (2006.01); B64C 27/43 (2006.01); B64C 27/51 (2006.01)
CPC B64C 27/43 (2013.01) [B64C 27/001 (2013.01); B64C 27/473 (2013.01); B64C 27/51 (2013.01); B64C 2027/005 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A rotor for a rotary wing aircraft having a single blade with a longitudinal pitch axis and that is hinge-mounted on a rotary shaft for rotating the rotor, the hinge being about an axis that is transversal relative to the rotary shaft, said rotary wing describing a cone when a pitch angle of the single blade is not zero, the rotor comprises a balancing flyweight device for balancing a resultant of a horizontal component of a lift force and a rotary drag force of the blade, the balancing flyweight device being mounted to rotate with the rotary wing about the rotary shaft, under an effect of a centrifugal force to which the balancing flyweight device is subjected while the rotary wing is rotating, a horizontal force is applied to the rotary shaft of the rotor and opposes the resultant with a magnitude that is a function of a position of a flyweight of the balancing flyweight device relative to the rotary shaft of the rotor.