Actuator for aviation applications

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, wherein two of the at least four sub-drives are dedicated to the same drive shaft in each case.

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.