Methods and apparatus for detecting and characterizing arc faults in an aerospace electric propulsion system and then coordinating the operation of various elements of the protection system to execute a fault-clearing sequence. In a current-based method, the arc is detected and characterized based on differential readouts from current sensors. The difference between currents measured at two ends of a protection zone are compared to a difference threshold. In a power-based method, the arc is detected and characterized based on differential readouts from voltage and current sensors. The differential voltage and current readouts are used to compute the respective powers at two ends of a protection zone. The difference between the respective powers is integrated over a period of time and then the integrated difference is compared to a difference threshold. A differential protection trip mode is invoked when the difference threshold is exceeded.


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    Title :

    Protection system for aircraft electric propulsion motor and motor controller


    Contributors:

    Publication date :

    2024-01-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01R Messen elektrischer Größen , MEASURING ELECTRIC VARIABLES



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    LACAUX FREDERIC / SOLODOVNIK EUGENE V / KHOZIKOV VYACHESLAV | European Patent Office | 2022

    Free access

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    LACAUX FREDERIC / SOLODOVNIK EUGENE V / KHOZIKOV VYACHESLAV | European Patent Office | 2022

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    FREDERIC LACAUX / EUGENE V SOLODOVNIK / VYACHESLAV KHOZIKOV | European Patent Office | 2022

    Free access

    Protection system for aircraft electric propulsion motor and motor controller

    LACAUX FREDERIC / SOLODOVNIK EUGENE V / KHOZYKOV VYACHESLAV | European Patent Office | 2022

    Free access