Helicopter with an anti-torque system

Patent metadata

Field	Value
Publication number	US-11780575-B2
Application number	US-201816765318-A
Country	US
Kind code	B2
Filing date	Dec 21, 2018
Priority date	Dec 22, 2017
Publication date	Oct 10, 2023
Grant date	Oct 10, 2023

Abstract

An anti-torque system (10) for a helicopter (1) is described that comprises: an electric power supply unit (15); at least one first rotor (17), operatively connected to an electric power supply unit (15) and operable by the electric power supply unit (15) so as to rotate with a first variable angular speed; and at least one second rotor (25) operatively connected to electric power supply unit (15) and operable by the electric power supply unit (15) so as to rotate with a second variable angular speed.

First claim

The invention claimed is:

1. A helicopter ( 1 ) comprising:
a fuselage ( 2 );
a first main rotor ( 4 ), which is adapted to generate, in use, the necessary lift for the flight of said helicopter ( 1 ) and to enable the forward/backward, upward/downward and lateral movement of said helicopter ( 1 ), and generating, in use, a first torque (C 1 ) on said fuselage ( 2 );
an anti-torque system ( 10 ) adapted to generate, in use, a second torque (C 2 ) having a main component in the same or opposite direction with respect to said first torque (C 1 ), so as to control the yaw angle of said helicopter ( 1 ); and
a tail portion ( 5 ) connected to said fuselage ( 2 );

said tail portion ( 5 ) comprising, in turn:
a tail boom ( 50 ) connected to said fuselage ( 2 );
a fin ( 6 ) protruding from an aft end of said tail boom ( 50 ) on the opposite side of said fuselage ( 2 ) and transversally with respect to said tail boom ( 50 ); and
a tailplane ( 7 ) projecting in cantilever fashion on both sides of said fin ( 6 );
said tail boom ( 50 ) being adapted to sustain the bending moments and the shear stress generated, in use, by the weight of said fin ( 6 ) and said tailplane ( 7 );
characterized in that said anti-torque system ( 10 ) integrated with said tail boom ( 50 ) and comprises;
an electric power supply unit ( 15 );
at least one second rotor ( 17 ) operatively connected to said electric power supply unit ( 15 ) and operable by said electric power supply unit ( 15 ) so as to rotate with a first variable angular speed; and
at least one third rotor ( 25 ) operatively connected to said electric power supply unit ( 15 ) and operable by said electric power supply unit ( 15 ) so as to rotate with a second variable angular speed;

said tail portion ( 5 ) comprising, in turn:
a plurality of walls ( 35 ) supporting respective said second and third rotors ( 17 , 25 );
a plurality of openings ( 37 ) delimited by said walls ( 35 ), passing across said tail portion ( 5 ) and having sufficient breadth to allow, in use, a correct supply of air to said second and third rotors ( 17 , 25 ).

2. The helicopter according to claim 1 , characterized in that it comprises a plurality of said second rotors ( 25 ) rotating about respective axes (C) staggered from one another.

3. The helicopter according to claim 2 , characterized in that at least one of said second rotors ( 25 ) is ducted by means of a relative duct ( 90 ).

4. The helicopter according to claim 2 , characterized by comprising a single duct ( 91 ), which ducts at least two second rotors ( 25 ).

5. The helicopter according to claim 1 , characterized in that said anti-torque system ( 10 ) is connected in a fixed way and integral to said tail portion ( 5 ).

6. The helicopter according to claim 1 , characterized in that said tailplane ( 7 ) is arranged at a free end of said fin ( 6 ) opposite to said aft end of said tail boom ( 50 ).

7. The helicopter of claim 1 , further comprising:
at least one power plant ( 100 ); and
a gearbox ( 101 ) drivable by said power plant ( 100 ) and operable to drive said first rotor ( 4 );

said electric power supply unit ( 15 ) comprising, in turn, an electric propulsion system ( 110 , 110 ′, 110 ″, 110 ′″) operatively connected with said power plant ( 100 ) and with said second and third rotor ( 17 , 25 ) to feed said second and third rotor ( 17 , 25 ) with electrical power.

8. The helicopter of claim 7 , characterized by comprising an electrical power distribution grid ( 103 ) electrically connected with said second and third rotor ( 17 , 25 ) to feed them with electrical power;
said electric propulsion system ( 110 , 110 ′, 110 ″, 110 ′″) feeding said electrical power distribution grid ( 103 ) with said electrical power.

9. The helicopter of claim 7 , characterized in that said electric propulsion system ( 110 , 110 ″) comprises a first electrical generator ( 111 , 111 ″) functionally interposed between said gearbox ( 101 ) and said second and third rotor ( 17 , 25 ).

10. The helicopter of claim 9 , characterized in that said first electrical generator ( 111 ) is a one-way electrical machine, which is capable to convert, in use, the mechanical power provided by said gearbox ( 101 ) in electrical power fed, in use, to said second and third rotor ( 17 , 25 ).

11. The helicopter of claim 9 , characterized in that said first electrical generator ( 111 ″) is a two-way electrical machine, which is capable:
either to convert, in use, the mechanical power provided by said gearbox ( 101 ) in electrical power fed, in use, to said second and third rotor ( 17 , 25 ); or
to convert, in use, the electrical power of said electrical power distribution grid ( 103 ) to said gearbox ( 101 ) and, therefore, to said first rotor ( 4 ).

12. The helicopter of claim 11 , characterized in that said electric propulsion system ( 110 , 110 ″) comprises an energy storage device ( 112 ″), which is electrically connected to said electrical power distribution grid ( 103 );
said energy storage device ( 112 ″) being charged, in use, by said electrical power distribution grid ( 103 ) during a normal operation of said first electrical generator ( 111 ″);
said energy storage device ( 112 ″) feeding, in use, said electrical power distribution grid ( 103 ) in case of failure of said first electrical generator ( 111 ″).

13. The helicopter of claim 7 , characterized in that said electric propulsion system ( 110 ′, 110 ′″) comprises at least one second electrical generator ( 120 ′, 120 ′″) functionally interposed between said power plant ( 100 ) and said electrical power distribution grid ( 103 ).

14. The helicopter of claim 13 , characterized by comprising a free-wheel ( 152 ) interposed between said power plant ( 100 ) and said gearbox ( 101 );
said electrical propulsion system ( 110 ′, 110 ′″) being connected to said power plant ( 100 ) in such a way that said free-wheel ( 152 ) is also interposed between said gearbox ( 101 ) and said electrical propulsion system ( 110 ′, 110 ′″).

15. The helicopter of claim 14 , characterized in that said second generator ( 120 ′) is a one-way electrical machine, which is capable to convert, in use, the mechanical power provided by said power plant ( 100 ) in electrical power fed, in use, to said second and third rotor ( 17 , 25 ).

16. The helicopter of claim 14 , characterized in that said second generator ( 120 ″) is a two-way electrical machine, which is capable:
either to convert, in use, the mechanical power provided by said power plant ( 100 ) in electrical power fed, in use, to said second and third rotor ( 17 , 25 ); or
to convert, in use, the electrical power of said electrical power distribution grid ( 103 ) to said power plant ( 100 ) and, therefore, to said first rotor ( 4 ).

17. The helicopter of claim 16 , characterized by in that said second generator ( 120 ′″) is integrated in said power plant ( 100 ).

18. The helicopter of claim 13 , when depending on claim 7 , characterized by comprising a further basic distribution grid ( 102 ) provided to electrically feed low power electrical loads ( 150 );
Said second generator ( 120 ′, 120 ′″) being a dual voltage generator, which can feed said electrical power distribution grid ( 103 ) and said further basic distribution grid ( 102 ) with two level of voltages.

19. The helicopter of claim 13 , said electric propulsion system ( 110 ′, 110 ′″) comprises an energy storage device ( 112 ′″), which is electrically connected t

Assignees

• Leonardo Spa

Inventors

• Brunetti Massimo
• Bottasso Luigi Maria
• Goh Chee Su
• Weller Gary

Classifications

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64C27/08

  with two or more rotors · CPC title

• B64C27/82 Primary

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title

• B64C27/14

  Direct drive between power plant and rotor hub · CPC title