Voltage controlled aircraft electric propulsion system

A method of operating an aircraft electric propulsion system comprising:

• monitoring, with a controller circuitry, a voltage and a current of a power supply bus supplying power to a load, the load comprising an electric propulsor configured to provide thrust for an aircraft;
• dynamically measuring an altitude of the aircraft;
• monitoring, with the controller circuitry, a thrust demand output for thrust of the electric propulsor;
• dynamically adjusting, with the controller circuitry, a voltage set point of the voltage of the power supply bus according to dynamic changes in the altitude of the aircraft by dynamically adjusting a weighting applied to the voltage set point according to the thrust demand output;
• maintaining, with the controller circuitry, a flow of the current on the power supply bus substantially constant as the altitude of the aircraft changes, by adjustment of the voltage set point;
• decreasing, with the controller circuitry, the voltage set point of the power supply bus as the altitude of the aircraft increases;
• and
• increasing, with the controller circuitry, the voltage set point of the power supply bus as the altitude of the aircraft decreases.

A non-transitory computer readable medium storing instructions executable by a processor circuitry, the computer readable medium comprising:

• instructions executable by the processor circuitry to control energization of a power supply bus with a generator power source, a stored energy power source or a combination thereof;
• instructions executable by the processor circuitry to control a voltage magnitude on the power supply bus to a first predetermined voltage, the power supply bus supplying power from the power supply bus to an electric propulsor of an aircraft;
• instructions executable by the processor circuitry to monitor an altitude of the aircraft, the altitude being a dynamically measured value indicative of a distance of the aircraft above sea level;
• instructions executable by the processor circuitry to monitor an output thrust of the electric propulsor;
• instructions executable by the processor circuitry to control the voltage magnitude on the power supply bus according to the altitude of the aircraft by dynamic adjustment of a weighting applied to a set point of the voltage magnitude according to the output thrust of the electric propulsor;
• and
• instructions executable by the processor circuitry to decrease the voltage magnitude as the aircraft increases in altitude.