Constant velocity drive rotary-wing aircraft rotor with torque splitting differential

• US 20030222171A1
• Filed: 03/20/2003
• Published: 12/04/2003
• Est. Priority Date: 03/28/2002
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Eurocopter
• Inventors: Zoppitelli, Elio, Cornille, Eric
• Granted Patent: US 6,712,313 B2
• Time in Patent Office: Days
• US Class Current: 244/10
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 27/41 with flapping hinge or universal joint, common to the blades
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: F16D 3/70 comprising elastic elements arranged in holes in one coupling part and surrounding pins on the other coupling part

Abstract

A constant velocity drive mechanism of a rotary-wing aircraft rotor, comprises a torque splitting differential mechanism, comprising a driving disc integral in rotation with a rotor mast and connected to each of two driven discs either side of the driving disc, by a least one connecting pin hinged to each of the discs by one of three ball joint connections. Each of the driven discs is connected to a hub of the rotor by at least one of two driving devices, each of which is also hinged to the hub, so as to drive the hub in rotation about a geometrical axis which can be inclined in all directions about the axis of rotation of the mast.

Claims

1. A rotary-wing aircraft rotor with constant velocity drive, comprising:

a rotor mast capable of being driven in rotation about a longitudinal axis of said mast,

a hub connected to said mast by a constant velocity drive mechanism and by a tilting arrangement, allowing pivoting of the hub as a whole about any flapping axis converging with the axis of the mast and perpendicular to said axis of the mast, in such a way that said hub is capable of being driven in constant velocity rotation by said mast, about a geometrical axis of rotation of the hub which may be inclined in any direction about the axis of the mast, and

at least two blades, each linked to said hub by a coupling retaining and hingeing the blade in pitch,

wherein said constant velocity drive mechanism comprises a differential mechanism for splitting static torque and allowing relative movement, in a plane perpendicular to said axis of the mast, between at least two devices for driving the hub, said differential mechanism comprising a set of three discs placed substantially one above another and substantially coaxial about said axis of the mast, a first disc of which, arranged between second and third discs of the set along said axis of the mast, is a driving disc, integral in rotation with said mast and connected to each of the second and third discs, which are driven, by at least one connecting pin having a longitudinal geometrical axis substantially parallel to said axis of the mast, and hinged to each of the discs in the set by one respectively of three ball joint connections substantially centred on the longitudinal geometrical axis of said connecting pin, each of the second and third discs being connected to the hub by at least one of said at least two driving devices which are each also hinged to the hub, so as to drive said hub in rotation about said geometrical axis of rotation of the hub.

2. A rotor according to claim 1, wherein the differential mechanism comprises at least two pins connecting the discs of the set, said connecting pins being regularly arranged in a circumferential direction about said axis of the mast.

3. A rotor according to claim 2, wherein the differential mechanism comprises at least two assemblies of at least two adjacent connecting pins per assembly, said assemblies of connecting pins being regularly distributed in a circumferential direction about said axis of the mast.

4. A rotor according to claim 1, wherein each connecting pin is hinged in the first disc by a central ball joint connection of larger diameter than a diameter common to two end ball joint connections of the said connecting pin and by each of which said connecting pin is hinged in one respectively of the second and third discs.

5. A rotor according to claim 4, wherein each of said three ball joint connections of each connecting pin further comprises a cylindrical laminated bearing, substantially coaxial with said connecting pin.

6. A rotor according to claim 1, wherein each connecting pin is a triple ball joint pin.

7. A rotor according to claim 6, wherein each of the three ball joint connections of each connecting pin also comprises a cylindrical laminated bearing, substantially coaxial with said connecting pin.

8. A rotor according to claim 1, wherein each of the second and third discs is mounted axially between two radial annular bearings, surrounding said mast and substantially coaxial about said axis of the mast, and allowing rotation, about said axis of the mast, of each of said second and third discs relative to said mast and to the first disc.

9. A rotor according to claim 8, wherein said radial annular bearings are selected from the group consisting of plain bearings and elements comprising one of cylindrical, truncated cone-shaped and spherical laminated elements.

10. A rotor according to claim 1, wherein at least one axial bush is fitted between a peripheral and axially offset portion of each disc in the set, in order to allow relative rotation, about said axis of the mast, of the second and third discs relative to the first disc and to said mast.

11. A rotor according to claim 10, wherein said axial bushes are selected from the group consisting of plain bushes and elements comprising one of cylindrical, truncated cone-shaped, and spherical laminated elements.

12. A rotor according to claim 1, wherein the first disc is made integral in rotation with said mast by internal axial splines engaging with external axial splines on an end portion of said mast, the end portion being spaced axially from a base portion of said mast, by which the mast is driven in rotation.

13. A rotor according to claim 1, wherein the second disc is arranged axially between the first disc and an external radial shoulder integral in rotation with said mast, while the third disc is arranged axially between the first disc and a device for axially preloading the set of three discs, and fitted to a free end of said mast.

14. A rotor according to claim 1, wherein each of the second and third discs supports two drive pins diametrically opposite relative to said axis of the mast, and by which the second and third discs are respectively connected to at least one of said driving devices, the drive pins of the second and third discs extending substantially in a common plane perpendicular to the axis of said mast.

15. A rotor according to claim 1, wherein the second disc drives in rotation, about said axis of the mast, and via two drive pins coaxial about a first diametral axis of said mast, a first driving device arranged as a first gimbal, mounted so as to pivot about said first diametral axis, which is substantially perpendicular to said axis of the mast, by two first bearings diametrically opposite relative to said axis of the mast;

and wherein the third disc drives in rotation, about said axis of the mast, and also via two drive pins coaxial about a second diametral axis of the mast, a second driving device, arranged as a second gimbal, mounted so as to pivot about said second diametral axis, which is substantially perpendicular to said axis of the mast and to said first diametral axis, and converging with the first diametral axis on said axis of the mast, by two second bearings diametrically opposite relative to said axis of the mast;

said first gimbal being in addition hinged to the hub by two first ball joint connections, diametrically opposite relative to said axis of the mast, and each centred substantially in a plane defined by said axis of the mast and said second diametral axis, and said second gimbal being in addition hinged to said hub by two second ball joint connections, diametrically opposite relative to said axis of the mast and each centred substantially in a plane defined by said axis of the mast and said first diametral axis;

whereby the gimbals, their pivoting bearings on the second and third discs and their ball joint connections providing hinging to the hub constitute the arrangement for tilting of the hub as a whole whilst belonging to the constant velocity drive mechanism of the hub.

16. A rotor according to claim 15, wherein the first and second bearings of the gimbals on the second and third discs and the ball joint connections hinging the gimbals to the hub comprise at least one element selected from the group consisting of cylindrical, spherical and truncated cone-shaped laminated elements.

17. A rotor according to claim 1, wherein each of the second and third discs drives in rotation, about said axis of the mast, and via two drive pins, two driving devices arranged as links diametrically opposite and aligned substantially tangentially relative to said axis of the mast, the driving devices being regularly arranged about said axis of the mast, so that each of two links driven by one of the second and third discs is between two links driven by another of the second and third discs, each drive link being hinged, at one of its ends, to one respectively of the two drive pins of one respectively of the second and third discs, and, at its other end, to an end fitting for attachment to the hub.

18. A rotor according to claim 17, wherein each drive link is equipped, at each of its two ends, with a ball joint connection, for hinging one end of said link to a drive pin of one of the second and third discs, and hinging another end of said link to an end fitting for attaching to the hub.

19. A rotor according to claim 18, wherein the ball joint connection comprises a laminated ball joint.

20. A rotor according to claim 1, wherein said devices for driving the hub in rotation from the second and third discs are connected to a hub casing, which surrounds said driving devices and said set of three discs, and which is attached to a hub plate connected to the blades and having a central opening through which said mast runs.

21. A rotor according to claim 20, wherein said hub plate is a plate in the form of a star with outward extending arms, one arm for each blade, and to each of which is fitted the coupling for retaining and hingeing its blade in pitch.

22. A rotor according to claim 1, wherein the hub is also connected to the mast by a least one member for elastic return of the hub to a rest position substantially perpendicular to said axis of the mast.

23. A rotor according to claim 22, wherein said elastic return member comprises at least one half of a central laminated spherical thrust bearing, of which one part is connected to the hub and at least one other part is integral in rotation with the mast.

24. A convertible aircraft comprising at least one tilting rotor movable from a first position in which the or each tilting rotor operates as an aeroplane propeller to a second position in which the or each tilting rotor operates as a helicopter main lifting rotor, the or each tilting rotor comprising:

a rotor mast capable of being driven in rotation about its longitudinal axis,

a hub connected to said mast by a constant velocity drive mechanism and by a tilting arrangement, allowing pivoting of the hub as a whole about any flapping axis converging with the axis of the mast and perpendicular to said axis of the mast, in such a way that said hub is capable of being driven in constant velocity rotation by said mast, about a geometrical axis of rotation of the hub which may be inclined in any direction about the axis of the mast, and

at least two blades, each linked to said hub by a coupling retaining and hingeing the blade in pitch,

wherein said constant velocity drive mechanism comprises a differential mechanism for splitting static torque and allowing relative movement, in a plane perpendicular to said axis of the mast, between at least two devices for driving the hub, said differential mechanism comprising a set of three discs placed substantially one above another and substantially coaxial about said axis of the mast, a first disc of which, arranged between second and third discs of the set along said axis of the mast, is a driving disc, integral in rotation with said mast and connected to each of the second and third discs, which are driven, by at least one connecting pin having a longitudinal geometrical axis substantially parallel to said axis of the mast, and hinged to each of the discs in the set by one respectively of three ball joint connections substantially centred on the longitudinal geometrical axis of said connecting pin, each of the second and third discs being connected to the hub by at least one of said at least two driving devices which are each also hinged to the hub, so as to drive it in rotation about said geometrical axis of rotation of the hub.