Aircraft hybrid electric propulsion architecture enabling modes of operation

A method of actively performing motor and electrical load management in a hybrid electrical propulsion (HEP) system of an aircraft, the method comprising:

• generating electrical power from an electrical system;
• delivering a first amount of the power to a propulsion system including a propulsor and an electric motor configured to drive the propulsor;
• generating, using the propulsion system, at least one of thrust or lift to operate the aircraft based on the first amount of power;
• delivering a second amount of the power to a plurality of electrical loads;
• and
• storing, in a HEP controller, a plurality of different voltage conversion operations corresponding to a plurality of different mission objectives of the aircraft;
• monitoring, by the HEP controller in signal communication with the electrical system and the propulsion system, a load demand of at least one electrical load of the plurality of electrical loads;
• and
• actively modifying one or both of the first amount of power and the second amount of power in response to changes in the load demand,
• wherein the actively modifying the one or both of the first amount of power or the second amount of power includes:
• determining an initiated mission system corresponding to a mission objective among the plurality of different mission objectives;
• determining the plurality of loads has a load demand that exceeds a load demand threshold associated with the initiated mission system;
• reducing the first amount of power delivered to the propulsion system to produce a first excess amount of power;
• delivering the first excess amount of power to a voltage conversion unit and performing a voltage conversion operation that corresponds to the initiated mission system of the mission objective to generate a converted first excess amount of power;
• outputting the converted first excess amount of power from the voltage conversion unit to increase the second amount of power and satisfy the load demand of the initiated mission system corresponding to the mission objective.