An aircraft main power generation system includes a rotor shaft (15), a main power generator (30) a permanent magnet generator (32), an exciter (26), an aircraft power bus (16), and a generator control unit (12). The generator control unit is configured to provide a control current to the exciter in response to a speed of the main power generator reaching a threshold speed and electrically couple the main power generator to the aircraft power bus in response to the speed of the main power generator reaching a minimum operating speed, the threshold speed being lower than the minimum operating speed; or provide a control current to the exciter in response to the speed of the main power generator reaching a predetermined speed and electrically coupling the main power generator to the aircraft power bus in response to a time period elapsing after the speed of the main power generator has reached the predetermined speed.


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    Titel :

    WOUND FIELD GENERATOR OVERVOLTAGE PREVENTION


    Weitere Titelangaben:

    ÜBERSPANNUNGSSCHUTZ FÜR EINEN GEWICKELTEN FELDGENERATOR
    PROTECTION CONTRE LES SURTENSIONS D'UN GÉNÉRATEUR DE CHAMP BOBINÉ


    Beteiligte:
    ROCHA DIEGO A (Autor:in) / PATEL DHAVAL (Autor:in) / DELL JONATHAN C (Autor:in) / DEFENBAUGH JOHN F (Autor:in) / BRUST ERIC A (Autor:in)

    Erscheinungsdatum :

    2021-12-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H02P CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS , Steuern oder Regeln von elektrischen Motoren, elektrischen Generatoren, dynamoelektrischen Umformern



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