US 12,434,824 B2
Rotor for an aircraft capable of hovering
Luigi Bottasso, Samarate (IT); Stefano Poggi, Samarate (IT); Phil Woody, Samarate (IT); Fabrizio Losi, Samarate (IT); Alessandro Nava, Samarate (IT); Sergio Sartori, Samarate (IT); Roberto Simonetta, Samarate (IT); Alessandro Airoldi, Samarate (IT); and Matteo Boiocchi, Samarate (IT)
Assigned to LEONARDO S.P.A., Rome (IT)
Appl. No. 18/007,579
Filed by LEONARDO S.P.A., Rome (IT)
PCT Filed May 26, 2021, PCT No. PCT/IB2021/054604
§ 371(c)(1), (2) Date Dec. 1, 2022,
PCT Pub. No. WO2021/260459, PCT Pub. Date Dec. 30, 2021.
Claims priority of application No. 20182377 (EP), filed on Jun. 25, 2020.
Prior Publication US 2023/0234701 A1, Jul. 27, 2023
Int. Cl. B64C 27/32 (2006.01); B64C 27/28 (2006.01); B64C 27/82 (2006.01); B64C 29/00 (2006.01); B64D 35/00 (2006.01); F16D 3/72 (2006.01)
CPC B64C 27/32 (2013.01) [B64C 27/28 (2013.01); B64C 27/82 (2013.01); B64C 29/0033 (2013.01); B64D 35/00 (2013.01); F16D 3/725 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A convertiplane comprising:
a fuselage extending along a first axis;
a pair of half-wings extending from respective side bands opposite one another of said fuselage along respective second axes;
a pair of rotors associated with said half-wings, rotatable around respective third axes and inclinable around a fourth axis orthogonal to said second and first axis between:
a first position in which said third axes are parallel to said first axis, which position is reached when said convertiplane is, in use, in an airplane configuration; and
a second position in which said third axes are orthogonal to said first axis, which position is reached when said convertiplane is, in use, in a helicopter configuration;
each said rotor comprising:
an input shaft rotatable around a respective fifth axis;
an output member rotatable around a respective said third axis;
a coupling element functionally interposed between said input shaft and said output member and adapted to transmit the motion from said input shaft to said output member;
said coupling element being configured to allow, in use, an inclination by a variable angle between the respective said respective fifth axis and said respective third axis;
characterized in that said coupling element comprises at least a first corrugated element made of an elastically deformable material;
said first corrugated element allowing said inclination through elastic deformation;
said input shaft being a control shaft of the respective said propeller rotatable around the respective said fifth axis;
said output member being a hub on which a plurality of respective blades are articulated and rotatable around a respective said third axis;
said coupling element is configured to allow, in use, said variable oscillation angle between respective said fifth and third axes;
wherein said coupling element is homokinetic; and/or
characterized in that said coupling element is torsionally rigid in a plane orthogonal to said fifth and third axis and flexurally yielding in at least one plane parallel to said fifth and third axis.