Examples provide a method and system for inhibiting aircraft electrical power system controller failsafe state cycling in air mode condition. The electrical power system controller can include a bus power control unit (BPCU) or a generator control unit (GCU). A failsafe cycling protection indicator, such as a software flag or hardware electronic latch has a first configuration to indicate failsafe cycling protection is enabled and a second configuration to indicate failsafe cycling protection is disabled. An internal low voltage power source generates an output voltage. If a monitor component monitoring the output voltage detects an undervoltage or overvoltage, the aircraft electrical power system controller goes into a failsafe state. A failsafe cycling component prevents the aircraft electrical power system controller from exiting the failsafe state if the failsafe cycling protection is enabled.


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    Title :

    POWER SYSTEM CONTROLLER FAILSAFE CYCLING PROTECTION


    Contributors:

    Publication date :

    2022-02-17


    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



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