Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: A method for detecting damages to a rotor of an aircraft, where the aircraft comprises actuators for active vibration reduction, may comprising one or more of the following steps: determining actuator variables in a reference flight of the aircraft; plotting the actuator variables of respective data range tiles determined in the reference flight of the aircraft in first coordinates of a coordinate system, wherein the coordinate system contains numerous data range tiles; obtaining the number of actuator variables in the reference flight of the aircraft that are located in each data range tile; eliminating the data range tiles that have a number of actuator variables lying below a limit value for this in the reference flight of the aircraft, by means of which a reference flight signature is created; and determining actuator variables for a flight-specific signature.

Abstract: A method for detecting damages to a rotor of an aircraft, where the aircraft comprises actuators for active vibration reduction, may comprising one or more of the following steps: determining actuator variables in a reference flight of the aircraft; plotting the actuator variables of respective data range tiles determined in the reference flight of the aircraft in first coordinates of a coordinate system, wherein the coordinate system contains numerous data range tiles; obtaining the number of actuator variables in the reference flight of the aircraft that are located in each data range tile; eliminating the data range tiles that have a number of actuator variables lying below a limit value for this in the reference flight of the aircraft, by means of which a reference flight signature is created; and determining actuator variables for a flight-specific signature.