Patent ID: 11958595
Assignee: AIRBUS HELICOPTERS TECHNIK GMBH
Field: Transport (Mechanical engineering)
Classification: CPC B  F | IPC B

Claim 15:
16. An actuator for adjusting rotor blades in a helicopter, the actuator comprising:
an electromechanical drive assembly connected to an output drive via a downstream transmission,
wherein the drive assembly is divided into sub-drives that can be operated independently,
wherein at least two sub-drives are spatially separated from one another in that the transmission is located between the at least two sub-drives,
wherein the transmission comprises at least two harmonic gearings coupled to one another by at least one first coupling element,
wherein a first harmonic gearing is located inside a non-rotating first housing,
wherein a second harmonic gearing is located inside a rotating second housing, wherein the second housing is connected to the output drive, and
wherein there are four sub-drives, and each of the at least four sub-drives is dedicated to a separate drive shaft.