Rotor and gyrocopter with said rotor

1. A rotor having a radius and comprising:

a rotor head; and

at least two rotor blades connectable to the rotor head, each rotor blade including a blade neck having a blade-connector region including two auxiliary flapping hinges spaced apart from one another in a radial longitudinal direction of the rotor blade and a flexurally elastic blade-neck region forming a virtual flapping hinge disposed substantially between the two auxiliary flapping hinges, the virtual flapping hinge being deformable in a flexurally elastic and curved fashion in response to a flapping motion,

wherein the blade-connector region includes at least one blade-connector arm and wherein respective blade-connector arms of the at least two rotor blades are joined to each other and overlap each other at a subregion, and wherein one of the auxiliary flapping hinges is disposed at the subregion.

2. The rotor as recited in claim 1 , further comprising a further flexurally elastic blade-neck region adjacent to and radially outward from the radially outer of the two auxiliary flapping hinges.

3. The rotor as recited in claim 2 , wherein the rotor is a hingeless rotor and wherein the further flexurally elastic blade-neck region forms a virtual lead-lag hinge.

4. The rotor as recited in claim 1 , wherein the rotor is a bearingless and hingeless rotor further comprising a virtual lead-lag hinge, and a torsionally flexible blade neck for bearingless blade angle adjustment.

5. The rotor as recited in claim 1 , wherein a flapping hinge distance of the rotor is greater than or equal to zero.

6. The rotor as recited in claim 1 , wherein a flapping hinge distance of the rotor is less than zero.

7. The rotor as recited claim 1 , wherein the virtual flapping hinge is disposed in a region of the blade neck between the two auxiliary flapping hinges.

8. The rotor as recited in claim 1 , wherein the two auxiliary flapping hinges simultaneously form two auxiliary lead-lag hinges, spaced apart from one another in a radial direction of the rotor blade, and wherein the rotor further comprises a virtual lead-lag hinge disposed between the two auxiliary lead-lag hinges and wherein the blade neck is deformable in flexurally elastic and curved fashion in response to a lead-lag motion of the rotor blade.

9. The rotor as recited in claim 8 , wherein the virtual lead-lag hinge is embodied in lead-lag-stiff fashion.

10. The rotor as recited in claim 1 , wherein at least one of the auxiliary flapping hinges includes a swivel joint.

11. The rotor as recited in claim 1 , wherein at least one of the auxiliary flapping hinges is formed by a flexurally elastic portion of the blade neck.

12. The rotor as recited in claim 1 , wherein at least one of the auxiliary flapping hinges is formed by a support device supporting the blade neck in the region of the auxiliary flapping hinge.

13. The rotor as recited in claim 1 , wherein the at least two rotor blades include common auxiliary flapping hinges disposed in a common blade-neck joining region.

14. The rotor as recited in claim 1 , wherein the at least two rotor blades each lie at an offset from one another of approximately 180 degrees with reference to the rotor disc and form a rotor blade pair,

wherein the rotor blade pair includes two common auxiliary flapping hinges and one common virtual flapping hinge.

15. The rotor as recited in one claim 1 , wherein the blade-connector region of the blade neck of a respective rotor blade is embodied in the form of a single blade-connector arm, the single blade-connector arm extends alongside an axis of the rotor axis and past it, and is joined to an intermediate portion of a respectively adjacent, similarly configured rotor blade.

16. The rotor as recited in claim 1 , wherein the blade-connector region of the blade neck, is embodied in the form of a blade-connector fork having at least two blade-connector arms discharging centrifugal-force.

17. The rotor as recited in claim 1 , and axis of the rotor extends between the at least two blade-connector arms.

18. The rotor as recited in claim 1 , the at least one blade-connector arm includes at least two blade-connector arms, at least one of which includes an arm end, embodied as a fork terminal, that engages in the region of one of the two auxiliary flapping hinges and is joined to a blade-connector arm region of a blade-connector arm of a respective other rotor blade.

19. The rotor as recited in claim 1 , wherein the at least one blade-connector arm is divided into at least two blade-connector arm segments located one above another in a direction of a rotor axis.

20. The rotor as recited in claim 1 , wherein the at least one blade-connector arms includes a fork having at least two blade-connector arms and wherein the rotor blades and at least one subregion receives centrifugal forces of the respective other rotor blade.

21. The rotor as recited in claim 20 , wherein the blade-connector arms of the rotor blades that are joined to one another via their blade-connector forks overlap at least in subregions.

22. The rotor as recited in claim 20 , wherein the at least two blade-connector arms extend in different planes.

23. The rotor as recited in claim 20 , wherein the blade-connector arms are strip- or plate-shaped.

24. The rotor as recited in one claim 1 , wherein the at least one rotor blade is nonrotatably joined in the region of the two auxiliary flapping hinges, via a torque-transmission element, to a rotor mast.

25. The rotor as recited in claim 24 , wherein the torque-transmission element engages the rotor blades at the subregion at a location at which least one of the auxiliary flapping hinges is located.

26. The rotor as recited in claim 1 , wherein the torque-transmission element is flexurally elastic in a flapping direction of the at least one rotor blade.

27. The rotor as recited in claim 1 , wherein the rotor blade has in the blade-connector region at least two centrifugal-force-discharge elements, spaced apart from one another in the longitudinal direction or centrifugal-force direction, of which at least one receives, during continuous operation of the rotor, the centrifugal forces occurring at the rotor blade.

28. The rotor as recited in claim 1 , wherein at least a portion of one of the two auxiliary flapping hinges is configured as a centrifugal element.

29. The rotor as recited in claim 1 , wherein the rotor blades are joined to one another in the region of their auxiliary flapping hinges, and at least a portion of one respective auxiliary flapping hinge embodied as a centrifugal-force-discharge element for at least one respective other rotor blade.

30. A rotorcraft having at least one rotor as recited in claim 1 .

31. The rotorcraft as recited in claim 30 , wherein the rotorcraft includes at least one of a helicopter and a tiltrotor helicopter.