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.


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    Titel :

    ACTUATOR FOR AVIATION APPLICATIONS


    Beteiligte:
    HAAR JAN (Autor:in) / ARNOLD UWE (Autor:in) / MEUNIER MARTIN (Autor:in) / WINTJEN CARSTEN (Autor:in) / MÜLLER MATTHIAS (Autor:in) / PFLÜGER WERNER (Autor:in)

    Erscheinungsdatum :

    29.06.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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