Transmission for rotor for an aircraft capable of hovering

Patent metadata

Field	Value
Publication number	US-11161602-B2
Application number	US-201716473701-A
Country	US
Kind code	B2
Filing date	Dec 29, 2017
Priority date	Dec 30, 2016
Publication date	Nov 2, 2021
Grant date	Nov 2, 2021

Abstract

A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element, which is rotatable about a first axis with respect to said stationary support structure with a first rotational speed. The rotor includes at least one blade, which is operatively connected with said rotative element; and a transmission group, which includes an output element rotatable about first axis with a second rotational speed different from first rotational speed.

First claim

The invention claimed is:

1. A rotor ( 3 , 3 ′, 3 ″) for an aircraft ( 1 ) capable of hovering, comprising:
a stationary support structure ( 10 );
a rotative element ( 11 ), which is rotatable about a first axis (A) with respect to said stationary support structure ( 10 ) with a first rotational speed (ω 2 );
a hub ( 12 ), which is rotationally integral to said rotative element ( 11 );
a ring ( 48 , 48 ′), which is connected to and angularly integral with said hub ( 12 ); and
at least one blade ( 13 ), which is operatively connected with said rotative element ( 11 ) and is articulated onto said hub ( 12 );
characterized by comprising a transmission group ( 33 ), which comprises an output element ( 36 , 36 ′, 36 ″) rotatable about said first axis (A) with a second rotational speed (o) 1 ) different from said first rotational speed (ω 2 );
said transmission group ( 33 ) comprising a first epicyclic gear train ( 37 , 37 ′, 37 ″);
said first epicyclic gear train ( 33 ) receiving, in use, the motion from said ring ( 48 , 48 ′) and driving in rotation, in use, said output element ( 36 , 36 ′, 36 ″) with said second rotational speed (ω 1 ).

2. The rotor of claim 1 , characterized by comprising:
a first gear ( 45 ), which is defined by said output element ( 36 , 36 ′, 36 ″) and is rotatable about said first axis (A);
a second gear ( 48 ) rotationally integral with and driven in rotation, in use, by said hub ( 12 ) about said first axis (A); and
at least one pair of third planet gears ( 46 ); and
a first carrier ( 47 ), which is connected to said third planet gears ( 46 );
said at least one pair of third planet gears ( 46 ) simultaneously meshing with said first gear ( 45 ) and said second gear ( 48 ), being rotatable about respective second axes (F) parallel and distinct from said first axis (A) and being mounted to revolute about said first axis (A).

3. The rotor of claim 2 , characterized by comprising a second epicyclic gearing ( 17 ), which comprises:
a sun gear ( 20 ) which is connectable to an output shaft of an additional transmission group ( 8 ) of said aircraft ( 1 ) and is rotatable about said first axis (A) with said first rotational speed (ω 2 );
a crown gear ( 23 ) which is defined by support structure ( 10 ) and is stationary about said first axis (A);
a plurality of additional planet gears ( 21 ) which simultaneously mesh with said sun gear ( 20 ) and said crown gear ( 23 ); and
a second carrier ( 22 ), which is connected to said additional planet gears ( 21 ) and to said rotative element ( 11 );
said additional planet gears ( 21 ) being rotatable about respective third axes (E) parallel to said first axis (A) and being mounted to revolve about said first axis (A).

4. The rotor of claim 3 , characterized in that said at least one pair of third planet gears ( 46 ) are stationary about said first axis (A) and are connected to said support structure ( 10 ).

5. The rotor of claim 3 , characterized in that said second carrier ( 47 ) and said output element ( 36 ′) are axially contained inside the axial size of said hub ( 12 ).

6. The rotor of claim 5 , characterized in that said at least one pair of third planet gears ( 46 ) are rotationally integral and driven in rotation by said sun gear ( 20 ).

7. The rotor of claim 1 , characterized in that said output element ( 36 , 36 ′, 36 ″) supports a source ( 30 ) of a magnetic field;
said hub ( 12 ) supporting an electric conductive element ( 32 ), which is operatively connected to said rotative element ( 11 );
said electric conductive element ( 32 ) being electromagnetically coupled with said source ( 30 ), so that an electromotive force is magnetically induced, in use, in said electric conductive element ( 32 ).

8. An aircraft ( 1 ) capable of hovering comprising:
a fuselage ( 2 ) to which said support structure ( 10 ) is fixed;
a main transmission group ( 6 ); and
a main rotor ( 3 , 3 ′, 3 ″) according to claim 1 .

Assignees

• Leonardo Spa

Inventors

• Bottasso Luigi
• Zocchi Antonio
• Brunetti Massimo
• Medici Luca
• Wang James
• Lucchi Giorgio

Classifications

• B64C27/12 Primary

  Rotor drives · CPC title

• B64C2027/003

  mounted on rotor hub, e.g. a rotary force generator · CPC title

• B64C27/001

  Vibration damping devices · CPC title