A system of a hybrid aircraft (10) includes a first gas turbine engine (20A), a second gas turbine engine (20B), a power source (16), and a controller. The first gas turbine engine (20A) includes a first electric machine (12B). The second gas turbine engine (20B) includes a second electric machine (12B). The controller is operable to determine an operating condition of the first gas turbine engine (20A) and the second gas turbine engine (20B) and to detect a change in a thrust command for the hybrid aircraft (10). The controller is further operable to determine an adjustment to the second electric machine (12B) to compensate for the change in the thrust command while the first gas turbine engine (20A) is operating in a fuel-driven mode and the second gas turbine engine (20B) is operating in an electrically-driven mode. At least a portion of electric power to perform the adjustment to the second electric machine (12B) is extracted from the power source (16).


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    Title :

    POWER CONTROL FOR DESCENT IN A HYBRID ELECTRIC PROPULSION SYSTEM


    Additional title:

    HYBRIDE ELEKTRISCHES ANTRIEBSENERGIEVETEILUNG FÜR SINKFLUG
    GESTION D'ÉNERGIE DE DESCENTE DE SYSTÈME PROPULSIF HYBRIDE ÉLECTRIQUE


    Contributors:

    Publication date :

    2023-05-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen



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