US 12,012,204 B2
Rotor for a hover-capable aircraft
Enrico Bellussi, Samarate (IT); Massimo Brunetti, Samarate (IT); Giovanni Facchini, Samarate (IT); Nicola Ostuni, Samarate (IT); Francesco Castelli Dezza, Samarate (IT); Marco Mauri, Samarate (IT); Steven Chatterton, Samarate (IT); and Nicola Toscani, Samarate (IT)
Assigned to LEONARDO S.P.A., Rome (IT); and POLITECNICO DI MILANO, Milan (IT)
Appl. No. 17/789,871
Filed by LEONARDO S.P.A., Rome (IT); and POLITECNICO DI MILANO, Milan (IT)
PCT Filed Dec. 28, 2020, PCT No. PCT/IB2020/062480
§ 371(c)(1), (2) Date Jun. 29, 2022,
PCT Pub. No. WO2021/137131, PCT Pub. Date Jul. 8, 2021.
Claims priority of application No. 19219995 (EP), filed on Dec. 30, 2019.
Prior Publication US 2023/0050072 A1, Feb. 16, 2023
Int. Cl. B64C 27/473 (2006.01); B64D 15/12 (2006.01); B64D 45/00 (2006.01); F16C 19/06 (2006.01); H01F 21/04 (2006.01); B64C 27/06 (2006.01)
CPC B64C 27/473 (2013.01) [B64D 15/12 (2013.01); B64D 45/00 (2013.01); F16C 19/06 (2013.01); H01F 21/04 (2013.01); B64C 27/06 (2013.01); F16C 2326/43 (2013.01)] 44 Claims
OG exemplary drawing
 
1. A rotor (3, 4) for a hover-capable aircraft (1), comprising:
a support (9) angularly fixed with respect to an axis (B, C) and housing an electrical power source (20);
a unit (11, 12) rotatable with respect to said support (9) about said axis (B, C) and housing an electrical load (21, 24) of the resistive type; and
a power supply system (19, 19′, 19″, 19″′, 19″″, 19″″′, 19″″″, 19″″″′) adapted to electrically power said electrical load (21, 24); said power supply system (19, 19′, 19″, 19″′, 19″″, 19″″′, 19″″″, 19″″″′), in turn, comprising:
at least a first rotary transformer (22) electrically interposed between said power source (20) and said electrical load (21, 24); said first rotary transformer (22), in turn, comprising:
a first winding (26) arranged on said support (9), electrically connected to said power source (20) and which can be electrically supplied with an alternating voltage at a frequency value;
a second winding (28) arranged on said unit (11, 12, 13), electromagnetically coupled to said first winding (26) and electrically connected to said electrical load (21, 24);
a stator (100) carried by said support (9), rotationally fixed with respect to said axis (B, C) and to which said first winding (26) is fixed; and
a rotor (101) operatively connected to said unit (11, 12) and to which said second winding (28) is fixed;
said power supply system (19, 19′, 19″, 19″′, 19″″, 19″″′, 19″″″, 19″″″′) comprising a capacitive circuit (50) electrically connected to said first rotary transformer (22), so as to reduce the reactive power absorbed by said first rotary transformer (22); characterized in that said stator (100) defines a seat (171) engaged by an appendage (140) of said rotor (101); said seat (171) being engaged with axial play by said appendage (140) when said rotor (101) is correctly positioned with respect to said stator (100); said seat (171) making axial contact with said appendage (140) when said stator (100) is positioned incorrectly in the axial direction.