Rotor blade coupling device of a rotor head for a rotorcraft

1. A rotor blade coupling device configured for coupling to a rotor mast to form a rotor head for a rotorcraft, the rotor blade coupling device comprising:

a rotor head centerpiece;

at least three rotor blade mountings mounted on the rotor head centerpiece and configured for accommodating at least three rotor blades lying in a rotor plane, each of the at least three rotor blade mountings configured for pivoting motion about a pivoting axis extending vertical to the rotor plane;

at least one connecting element between adjacent rotor blade mountings, the at least one connecting element formed as a damping device; and

a transfer element crossing a rotor blade mounting and configured for coupling to at least one damping device, the transfer element at least sectionally accommodated by the damping device,

wherein the transfer element is configured and arranged to directly and functionally connect with two adjacent damping devices through coupling with each of the two adjacent damping devices and forming an integrated part of the two adjacent damping devices,

wherein the transfer element is tiltablely mounted relative to the rotor blade mountings by rocker bearings,

wherein the damping device is a plate damper configured and arranged to accommodate at least two transfer elements, the at least two transfer elements spaced apart and crossing adjacent rotor blade mountings, and

wherein the rocker bearings are more rigid in a crossing region of the rotor blade mountings than the plate dampers arranged between the rotor blade mountings.

2. The rotor blade coupling device according to claim 1 , wherein the rocker bearings are more rigid linearly in a rotational direction of the rotor blades or are more rigid along a rotor blade pitch axis.

3. The rotor blade coupling device according to claim 1 , wherein the plate damper has a rigidity between 0.5 kN/mm and 10 kN/mm.

4. The rotor blade coupling device according to claim 1 , wherein the plate damper has a rigidity between 1 kN/mm and 4 kN/mm.

5. The rotor blade coupling device according to claim 1 , wherein the rocker bearings are at least three times more rigid in a crossing region of the rotor blade mountings than the plate dampers arranged between the rotor blade mountings.

6. The rotor blade coupling device according to claim 5 , wherein the rocker bearings are at least three times more rigid linearly in a rotational direction of the rotor blades or are more rigid along a rotor blade pitch axis.

7. The rotor blade coupling device according to claim 1 , wherein the rocker bearings are at least five times more rigid in a crossing region of the rotor blade mountings than the plate dampers arranged between the rotor blade mountings.

8. The rotor blade coupling device according to claim 7 , wherein the rocker bearings are at least five times more rigid linearly in a rotational direction of the rotor blades or are more rigid along a rotor blade pitch axis.

9. A rotor head comprising a rotor blade coupling device according to claim 1 .

10. A rotor blade coupling device configured for coupling to a rotor mast to form a rotor head for a rotorcraft, the rotor blade coupling device comprising:

a rotor head centerpiece;

at least three rotor blade mountings mounted on the rotor head centerpiece and configured for accommodating at least three rotor blades lying in a rotor plane, each of the at least three rotor blade mountings configured for pivoting motion about a pivoting axis extending vertical to the rotor plane;

at least one connecting element between adjacent rotor blade mountings, the at least one connecting element formed as a plate damper; and

a transfer element crossing a rotor blade mounting and configured for coupling to at least one plate damper, the transfer element mounted by a rocker bearing and at least sectionally accommodated by the plate damper;

wherein the transfer element is configured and arranged to directly and functionally connect with two adjacent plate dampers through coupling with each of the two adjacent plate dampers and forming an integrated part of the two adjacent plate dampers; and

wherein the rocker bearings are more rigid in a crossing region of the rotor blade mountings than the plate dampers arranged between the rotor blade mountings.

11. The rotor blade coupling device according to claim 10 , wherein the rotorcraft is a direct-lift machine or a helicopter.

12. The rotor blade coupling device according to claim 10 , wherein the rocker bearing is a spherical rocker bearing having at least one elastomer layer.

13. The rotor blade coupling device according to claim 10 , wherein the rocker bearings are more rigid linearly in a rotational direction of the rotor blades or are more rigid along a rotor blade pitch axis.

14. The rotor blade coupling device according to claim 10 , wherein the plate damper has a rigidity between 1 kN/mm and 4 kN/mm.

15. The rotor blade coupling device according to claim 10 , wherein the rocker bearings are at least three times more rigid in a crossing region of the rotor blade mountings than the plate dampers arranged between the rotor blade mountings.

16. The rotor blade coupling device according to claim 15 , wherein the rocker bearings are at least three times more rigid linearly in a rotational direction of the rotor blades or are more rigid along a rotor blade pitch axis.

17. A rotor head comprising a rotor blade coupling device according to claim 10 .