A method of controlling an electric propulsion system (5) of an aircraft (1). The propulsion system comprising an electric motor (10) configured to drive a variable pitch propulsor (12). The method comprises determining a commanded thrust setting; determining one or more flight parameters; determining either a corresponding rotor governor speed and motor torque set-point, or a corresponding motor speed and rotor pitch angle set point, which provides the commanded thrust setting at the determined flight parameter having a maximum propulsion system efficiency; and controlling the rotor governor and electric motor in accordance with the determined respective set-points.


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    Title :

    Aircraft electric propulsion system control method


    Publication date :

    2021-12-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English



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