An adaptive aircraft electrical power distribution system includes an aircraft power source, a power connector, an aircraft power distribution bus, and a bidirectional power controller. The aircraft power source is operable to generate and supply electrical power. The power connector is mounted on a fuselage of the aircraft. The aircraft power distribution bus is operable to distribute electrical power to an aircraft electrical load. The bidirectional power controller is mounted in the aircraft and is electrically coupled to the aircraft power source, the aircraft power connector, and the aircraft power distribution bus. The bidirectional power controller is configured to: sense when the aircraft power source is generating and supplying electrical power, sense when electrical power is being supplied to the power connector from an external power source, and selectively couple at least one of the aircraft power source or the power connector to the aircraft power distribution system.


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    Title :

    ADAPTIVE AIRCRAFT ELECTRICAL POWER DISTRIBUTION SYSTEM


    Contributors:

    Publication date :

    2021-10-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H04W WIRELESS COMMUNICATION NETWORKS , Drahtlose Kommunikationsnetze



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