Transmission unit of an anti-torque rotor for a helicopter

Patent metadata

Field	Value
Publication number	US-12006028-B2
Application number	US-202017619771-A
Country	US
Kind code	B2
Filing date	May 26, 2020
Priority date	Jun 17, 2019
Publication date	Jun 11, 2024
Grant date	Jun 11, 2024

Abstract

An anti-torque rotor includes a mast rotatable about a first axis; a plurality of blades extending along respective second axes; and a control element sliding along the first axis with respect to the mast, integrally rotatable with said mast, and connected to said blades. A control rod slides axially along first axis and is angularly fixed with respect to said first axis. A connection element is interposed between the control rod and the control element and is configured to enable the relative rotation of said control element with respect to the control rod about the first axis. A transmission unit is available in an active configuration or an inactive configuration. The transmission unit has an annular ridge axially and angularly integral with the control rod and a seat engaged by the ridge and angularly integral with the control element.

First claim

The invention claimed is:

1. An anti-torque rotor ( 4 ′) for a helicopter ( 1 ), comprising:
a mast ( 6 ), rotatable about a first axis (A);
a plurality of blades ( 8 ), hinged on said mast ( 6 ), extending along respective second axes (B) transversal to said first axis (A) and rotatable about respective said second axes (B) to alter the respective angles of attack;
a control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ), integrally rotating with said mast ( 6 ), and operatively connected to said blades ( 8 ) to cause the rotation of said blades ( 8 ) about respective said second axes (B) following a translation of said element ( 16 ) along said axis (A);
a control rod ( 10 ), sliding axially along said first axis (A) with respect to said mast ( 6 ) and angularly fixed with respect to said first axis (A);
a first bearing ( 17 ), interposed between said control rod ( 10 ) and said control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ) and integrally with said control rod ( 10 ), and configured to enable the relative rotation of said control element ( 16 ) with respect to said control rod ( 10 ) about said first axis (A); and
a transmission unit ( 45 ), which is operatively connected to said control rod ( 10 ) and to said control element ( 16 );

said transmission unit ( 45 ) being selectively available:
in an active configuration, wherein said transmission unit ( 45 ) causes said control element ( 16 ) to slide, following the translation of said control rod ( 10 ), along said first axis (A); or
in an inactive configuration, wherein said transmission unit ( 45 ) is disengaged from said control element ( 16 );
wherein said transmission unit ( 45 ) being arranged in said active configuration in the event of failure of said first bearing ( 17 ), wherein said bearing ( 17 ) is no longer able to transmit an axial load from said rod ( 10 ) to said control element ( 16 ), causing the axial translation in both directions of said element ( 16 ), following the axial translation of said rod ( 10 );
said transmission unit ( 45 ) being arranged in said inactive configuration when said first bearing ( 17 ) correctly allows relative rotation of said element ( 16 ) and said rod ( 10 ) and prevents any relative translation between said element ( 16 ) and said rod ( 10 );
said transmission unit ( 45 ), in turn, comprising:
an annular ridge ( 61 ) axially integral with said control rod ( 10 ) and radially projecting from a cylindrical body ( 60 ); and
a seat ( 64 ) engaged by said ridge ( 61 ) and angularly and axially integral with said control element ( 16 );

characterized in that said rotor comprises a second bearing ( 100 , 101 ) interposed between said ridge ( 61 ) and said seat ( 64 );
said rotor ( 4 ′) further comprising detection means ( 50 );
said detection means ( 50 ), in turn, comprising a first sensor ( 52 ) adapted to generate a signal associated with the fact of said transmission unit ( 45 ) being in said active configuration.

2. The rotor according to claim 1 , characterized in that said ridge ( 61 ) engages said seat ( 64 ) with axial play, when said transmission unit ( 45 ) is in the inactive configuration;
said ridge ( 61 ) making contact, in use, with said seat ( 64 ), when said transmission unit ( 45 ) is in the active configuration.

3. The rotor according to claim 1 , characterized in that said ridge ( 61 ) and said seat ( 64 ) have respective trapezoidal profiles in a plane containing said first axis (A).

4. The rotor according to claim 1 , characterized in that at least one of said ridge ( 61 ) and said seat ( 64 ) is, at least partially, coated with an antifriction material.

5. The rotor according to claim 1 , characterized in that said transmission unit ( 45 ) comprises:
a sleeve ( 90 ) mounted coaxially on said control rod ( 10 ); and
a ring ( 63 ) mounted on said control element ( 16 ) and defining said seat ( 64 ) open towards said ridge ( 61 ).

6. The rotor according to claim 1 , characterized in that said first bearing ( 17 ) is a first antifriction bearing ( 17 );
said first bearing ( 17 ), in turn, comprising:
a first ring ( 30 ) integrally rotating with said control element ( 16 ) about said first axis (A); and
a second ring ( 31 ) radially internal to said first ring ( 30 ) with respect to said first axis (A) and integrally sliding with said control rod ( 10 ) along said first axis (A).

7. The rotor according to claim 6 , further comprising:
an interface ( 120 ) made of an antifriction material interposed between said control rod ( 10 ) and said second ring ( 31 ) of said first bearing ( 17 ), so as to enable the rotation of said first bearing ( 17 ) with respect to said control rod ( 10 ) about said first axis (A); and
a tubular element ( 90 ) radially interposed between said control rod ( 10 ) and said second ring ( 31 ), and axially sliding integrally with said control rod ( 10 ) and said second ring ( 31 );
said interface ( 120 ) comprising at least a first surface ( 94 ) of said tubular element ( 90 ), which is arranged is contact with said control rod ( 10 ), so as to enable the rotation of said tubular element ( 90 ) jointly with first bearing ( 17 ), with respect to said control rod ( 10 ).

8. The rotor according to claim 7 , characterized in that said interface ( 120 ) comprises a second surface ( 18 ) of said control rod ( 10 ) having an axial extension and arranged in contact with said first surface ( 94 ).

9. The rotor according to claim 7 , characterized in that said second ring ( 31 ) is axially blocked between said tubular element ( 90 ) and a radially projecting ridge ( 92 ) of said tubular element ( 90 ).

10. The rotor according to claim 9 , characterized in that said detection means ( 50 ) comprise:
a second sensor ( 53 ) adapted to detect the rotation of said tubular element ( 90 ); and/or
a third sensor ( 51 ) adapted to detect at least one of the temperature and acceleration of said first connection element ( 16 ) and/or of said tubular element ( 90 ).

11. A helicopter comprising:
a fuselage ( 2 );
a main rotor ( 3 ); and
an anti-torque rotor ( 4 , 4 ′) according to claim 1 .

12. An anti-torque rotor ( 4 , 4 ′) for a helicopter ( 1 ), comprising:
a mast ( 6 ), rotatable about a first axis (A);
a plurality of blades ( 8 ), hinged on said mast ( 6 ), extending along respective second axes (B) transversal to said first axis (A) and rotatable about respective said second axes (B) to alter the respective angles of attack;
a control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ), integrally rotating with said mast ( 6 ), and operatively connected to said blades ( 8 ) to cause the rotation of said blades ( 8 ) about respective said second axes (B) following a translation of said element ( 16 ) along said axis (A);
a control rod ( 10 ), sliding axially along said first axis (A) with respect to said mast ( 6 ) and angularly fixed with respect to said first axis (A);
a connection element ( 17 ), interposed between said control rod ( 10 ) and said control element ( 16 ), sliding along said first axis (A) with respect to said mast ( 6 ) and integrally with said control rod ( 10 ), and configured to enable the relative rotation of said control element ( 16 ) with respect to said control rod ( 10 ) about said first axis (A); and
a transmission unit ( 45 ), which is operatively connected to said control rod ( 10 ) and to said control element ( 16 );
said transmission unit ( 45 ) being selectively available:
in an active configuration, wherein said transmission unit causes said control element

Assignees

• Leonardo Spa

Inventors

• Delli Paoli Michele
• Nannoni Fabio
• Vanni Roberto

Classifications

• B64C27/82

  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

• B64C27/12

  Rotor drives · CPC title

• B64C27/78 Primary

  in association with pitch adjustment of blades of anti-torque rotor · CPC title