Actuator for use in aviation

1. An actuator for a rotor blade adjustment, comprising:

an electromechanical drive unit connected with an output drive via a gearbox, wherein the drive unit is connected to the gearbox via at least one input shaft; and

wherein the drive unit comprises at least a first partial drive and a second partial drive that can be operated independently from one another,

wherein the first partial drive, the gearbox, and the second partial drive are coaxial with, and arranged axially along, the at least one input shaft such that the gearbox is located between the first partial drive and the second partial drive to create a barrier between the first partial drive and the second partial drive, and

wherein the electromechanical drive unit further comprises third and fourth partial drives, wherein the first and third partial drives are located on a first side of the gearbox, and wherein the second and fourth partial drives are located on a second side of the gearbox.

2. The actuator of claim 1 , wherein the first and second partial drives comprise an electric motor with six phases.

3. The actuator of claim 1 , wherein the first and second partial drives each include an electric motor with three phases.

4. The actuator of claim 1 , wherein the at least one input shaft comprises a common input shaft associated with the first and second partial drives.

5. The actuator of claim 4 , wherein a separating clutch is located between the input shaft and at least one of the first and second partial drives, and wherein the separating clutch is configured to interrupt a mechanical connection of the input shaft.

6. The actuator of claim 1 , wherein the at least one input shaft is one of two input shafts, wherein one of the input shafts is associated with the first partial drive located on the first side of the gearbox, and wherein the other input shaft is associated with the second partial drive situated on the second side of the gearbox, and wherein the gearbox connects the first and second partial drives with the output drive.

7. The actuator according to claim 1 , wherein the gearbox comprises multiple gear speeds.

8. The actuator of claim 1 , wherein the gearbox comprises a planetary gear or a cycloidal gear.

9. An actuator for aviation applications, the actuator comprising:

a drive unit having at least a first partial drive and a second partial drive;

a gearbox connected to the drive unit, wherein the drive unit is connected to the gearbox via at least one input shaft; and

an output drive connected to the gearbox,

wherein the first partial drive, the gearbox, and the second partial drive are coaxial with, and arranged axially along, at least one input shaft such that the first partial drive is located on a first side of the gearbox and the second partial drive is located on a second side of the gearbox and such that the gearbox forms a barrier between the first partial drive and the second partial drive, and

wherein the drive unit further comprises third and fourth partial drives connected to the gearbox.

10. The actuator of claim 9 , wherein the first side is opposite of the second side.

11. The actuator of claim 9 , wherein the first and second partial drives each comprise an electric motor with six phases.

12. The actuator of claim 9 , wherein the first and third partial drives are located on the first side of the gearbox, and wherein the second and fourth partial drives are located on the second side of the gearbox.

13. The actuator of claim 9 , wherein the first, second, third, and fourth partial drives each comprise an electric motor with three phases.

14. The actuator of claim 9 , wherein the at least one input shaft comprises a common input shaft associated with the first and second partial drives.

15. The actuator of claim 9 , further comprising a separating clutch located between the first partial drive and the gearbox.

16. The actuator of claim 9 , wherein the gearbox comprises multiple gear speeds.