Helicopter kit

Patent metadata

Field	Value
Publication number	US-11247771-B2
Application number	US-201916763802-A
Country	US
Kind code	B2
Filing date	Jun 28, 2019
Priority date	Jul 27, 2018
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

A kit is described that comprises a device adapted to dampen the vibrations transmitted by the rotor to the fuselage; the device comprises two first elements movable along a first axis; two second elements rotatable about the first axis; a first inerter with a first female screw, a first screw, and first rollers rotatable about respective second axes and around the first axis with respect to the first female screw and first screw; a second inerter with a second female screw, a second screw operatively connected to the second female screw; and a plurality of second rollers rotatable about second axes and around the first axis with respect to the second female screw and second screw; the first and second female screws defining the first threaded elements, and the first and second screws defining the second threaded elements; or the first and second screws defining the first threaded elements and the first and second female screws defining the second threaded elements.

First claim

The invention claimed is:

1. A kit ( 1 , 1 ′) for a helicopter ( 2 ), said helicopter ( 2 ) comprising a fuselage ( 3 ) and a rotor ( 4 );
said kit ( 1 , 1 ′) comprising at least one device ( 15 ) designed to dampen the vibrations transmitted from said rotor ( 4 ) to said fuselage ( 2 ) and be interposed between said fuselage ( 2 ) and said rotor ( 4 );
characterised in that said device ( 15 , 15 ′), in turn, comprises:
a pair of first threaded elements ( 21 a , 21 b ; 20 a , 20 b ) movable parallel along a first axis (B) and adapted to vibrate parallel to said first axis (B);
a pair of second threaded elements ( 20 a , 20 b ; 21 a , 21 b ) rotatable about said first axis (B) and operatively connected to respective said first threaded elements ( 21 a , 21 b ; 20 a , 20 b ), so as to, in use, rotationally vibrate about said first axis (B);
a first inerter ( 16 ); and
a second inerter ( 17 );
said first inerter ( 16 ), in turn, comprising:
a first female screw ( 21 a );

a first screw ( 20 a ) operatively connected to said first female screw ( 21 a ); and
a plurality of first threaded rollers ( 22 a ), which are screwed on said first female screw and first screw ( 21 a , 20 a ); said first rollers ( 22 a ) being rotatable about respective second axes (C) parallel to and separate from said first axis (B) with respect to said first female screw and first screw ( 21 a , 20 a ), and being rotatable about said first axis (B) with respect to said first female screw and first screw ( 21 a , 20 a );
said second inerter ( 17 ), in turn, comprising:
a second female screw ( 21 b );
a second screw ( 20 b ) operatively connected to said second female screw ( 21 b ); and
a plurality of second threaded rollers ( 22 b ), which are screwed on said second female screw and second screw ( 21 b , 20 b ); said second rollers ( 22 b ) being rotatable about respective second axes (C) parallel to and separate from said first axis (B) with respect to said second female screw and second screw ( 21 b , 20 b ), and being rotatable about said first axis (B) with respect to said second female screw and second screw ( 21 b , 20 b );
said first and second female screws ( 21 a , 21 b ) defining said first threaded elements ( 21 a , 21 b; 20 a , 20 b ), and said first and second screws ( 20 b , 20 a ) defining said second threaded elements ( 20 a , 20 b ; 21 a , 21 b ); or
said first and second screws ( 20 b , 20 a ) defining said first threaded elements ( 21 a , 21 b ; 20 a , 20 b ) and said first and second female screws ( 21 a , 21 b ) defining said second threaded elements ( 20 a , 20 b ; 21 a , 21 b ).

2. The kit according to claim 1 , characterised in that said second threaded elements ( 20 a , 20 b ; 21 a , 21 b ) are configured so as to be rotatable with mutually opposite directions of rotation; and/or
characterised in that said first axes (B) of said first and second inerters ( 16 , 17 ) coincide with each other and define an extension axis of said device ( 15 , 15 ′); and/or
characterised in that said second rotation axes (C) of said first and second rollers ( 22 a , 22 b ) coincide with each other.

3. The kit according to claim 1 , characterised in that said first threaded elements ( 21 a , 21 b ) of said first and second inerters ( 16 , 17 ) are together integrally movable parallel to said first axis (B).

4. The kit according to any one of the preceding claim 1 , characterised in that the threads of said first threaded element ( 21 a ), of said second threaded element ( 20 a ) and of said first rollers ( 22 a ) of said first inerter ( 16 ) have a first handedness;
the threads of said first threaded element ( 21 b ), of said second threaded element ( 20 b ) and of said second rollers ( 22 b ) of said second inerter ( 17 ) have the same said first handedness.

5. The kit according to claim 1 , characterised in that it comprises a first anchoring element ( 30 ) connectable in an articulated manner to said rotor ( 4 );
said first threaded elements ( 21 a , 21 b ) being constrained to said first anchoring element ( 30 ).

6. The kit according claim 1 , characterised in that the threads of said first threaded element ( 21 a ), of said second threaded element ( 20 a ) and of said first rollers ( 22 a ) of said first inerter ( 16 ) have a first handedness; and the threads of said first threaded element ( 21 b ), of said second threaded element ( 20 b ) and of said second rollers ( 22 b ) of said second inerter ( 17 ) have a second handedness, opposite to said first handedness.

7. The kit according to claim 1 , characterised in that said first and second inerters ( 16 , 17 ) have the same inertance.

8. The kit according to claim 7 , characterised in that it comprises:
a first flywheel ( 40 a , 40 a ′) angularly integral with said second threaded element ( 20 a ) of said first inerter ( 16 ); and/or
a second flywheel ( 40 b , 40 b ′) angularly integral with said second threaded element ( 20 b ) of said second inerter ( 17 ).

9. The kit according to claim 1 , characterised in that it comprises:
a first anchoring element ( 30 ) connectable in an articulated manner to said rotor ( 4 );
a first bearing ( 41 a ), which supports said second threaded element ( 20 a ) of said first inerter ( 16 ) in an angularly movable manner about said first axis (B);
a second anchoring element ( 31 ) connectable in an articulated manner to said fuselage ( 3 ); and
a second bearing ( 41 b ), which supports said second threaded element ( 20 b ) of said second inerter ( 17 ) in an angularly movable manner about said first axis (B).

10. The kit according to claim 9 , characterised in that said first inerter ( 16 ) is interposed between said first anchoring element ( 30 ) and said second inerter ( 17 );
said second inerter ( 17 ) being interposed between said first inerter ( 16 ) and said second anchoring element ( 31 ).

11. The kit according to claim 1 , characterised in that it comprises:
a second anchoring element ( 31 ) connectable in an articulated manner to said fuselage ( 3 ); and
two bearings ( 41 a ′, 41 b ′) interposed between said second anchoring element ( 31 ) and respective said second threaded elements ( 20 a , 20 b ), and configured to support the loads directed along said first axis (B) discharged from said second threaded elements ( 20 a , 20 b ).

12. The kit according to claim 11 , characterised in that it comprises:
a first body ( 61 ′) fastened to said first support element ( 30 ) and defining said first threaded elements ( 21 a ) of said first inerter ( 16 );
a second body ( 62 ′) rotatable about said first axis (B) and defining said second threaded element ( 20 a ) of said second inerter ( 16 );
a third body ( 71 ′) fastened to said first support element ( 30 ) and defining said first threaded elements ( 21 b ) of said second inerter ( 17 ); and
a fourth body ( 72 ′) rotatable about said first axis (B) and defining said second threaded element ( 20 b ) of said second inerter ( 17 );
said second body ( 62 ′) being at least partially housed inside said first body ( 61 ′);
said third body ( 71 ′) being at least partially housed inside said second body ( 62 ′); and
said fourth body ( 72 ′) being at least partially housed inside said third body ( 61 ′).

13. A helicopter comprising:
said fuselage ( 2 );
said rotor ( 4 );
a support casing ( 5 ) of said rotor ( 4 ); and
a plurality of connecting rods ( 7

Assignees

• Leonardo Spa

Inventors

• Bottasso Luigi
• Colombo Attilio
• Masarati Pierangelo
• Tamer Aykut
• Quaranta Giuseppe

Classifications

• F16F2232/06

  Translation-to-rotary conversion · CPC title

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title

• F16F2222/08

  Inertia · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title

• F16F15/02

  Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems ({F16F15/005 takes precedence } ; layered products B32B; suppression of vibration in ships B63; {relieving load on bearings, using magnetic means F16C39/06}) · CPC title