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.
Aircraft electric propulsion system control method
2021-12-01
Patent
Electronic Resource
English