CPC B64C 27/68 (2013.01) [B64C 27/04 (2013.01)] | 20 Claims |
1. 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 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, wherein the actuator also comprises a third harmonic gearing and a fourth harmonic gearing, which are located axially between the first and second harmonic gearings, wherein the at least one coupling element comprises a first coupling element and a second coupling element, the first coupling element couples the first and third harmonic gearings, and the second coupling element couples the second and fourth harmonic gearings, and wherein the first and second coupling elements are connected to one another for conjoint rotation.
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