Method for monitoring an energy level of an electrical energy source of a hybrid power plant for an aircraft

An electrical energy source for equipping an aircraft, the aircraft comprising a hybrid power plant and a lift rotor rotated by the hybrid power plant via a mechanical transmission system, the hybrid power plant comprising at least one heat engine and at least one electric machine, the electrical energy source being configured to be electrically connected to the at least one electric machine via an electrical connection system, the electrical energy source being capable of delivering a reference electrical power for a predetermined reference time period for a predetermined reference charge level, the electrical energy source comprising:

• at least one electrical energy storage device;
• at least one sensor;
• and
• calculator comprising at least one processor and at least one memory storing instructions that, when executed by the at least one processor, cause the calculator, when the electrical energy source equips the aircraft, to:
• acquire at least one parameter of the electrical energy source via the at least one sensor;
• calculate a main consumption time period wherein the electrical energy source is able to supply an electric current carrying the reference electrical power, as a function of the at least one parameter of the electrical energy source;
• cause a display unit of the aircraft to display a main display of main symbols indicating the main consumption time period;
• determine, based on information received from at least one sensor or avionics system of the aircraft, at least one characteristic of the aircraft;
• estimate at least one rate of sink and at least one distance that is reachable using only electrical energy that the electrical energy source can deliver as a function of the at least one parameter of the electrical energy source and the at least one characteristic of the aircraft;
• and
• cause the display unit to display a descent display of descent symbols representing at least one trajectory of descent of the aircraft as a function of the rate of sink and the reachable distance.

An aircraft comprising:

• a hybrid power plant comprising at least one heat engine and at least one electric machine;
• a lift rotor rotated by the hybrid power plant via a mechanical transmission system;
• a display unit;
• an electrical energy source electrically connected to the at least one electric machine via an electrical connection system and capable of delivering a reference electrical power for a predetermined reference time period for a predetermined reference charge level, the electrical energy source comprising:
• at least one electrical energy storage device;
• at least one sensor;
• and
• calculator comprising at least one processor and at least one memory storing instructions that, when executed by the at least one processor, cause the calculator to:
• acquire at least one parameter of the electrical energy source via the sensor;
• calculate a main consumption time period wherein the electrical energy source is able to supply an electric current carrying the reference electrical power, as a function of the parameter of the electrical energy source;
• cause the display unit to display a main display of main symbols indicating the main consumption time period;
• determine, based on information received from at the least one sensor or avionics system of the aircraft, at least one characteristic of the aircraft;
• estimate at least one rate of sink and at least one distance that is reachable using only electrical energy that the electrical energy source can deliver as a function of the parameter of the electrical energy source and the characteristic of the aircraft;
• and
• cause the display unit to display a descent display of descent symbols representing at least one trajectory of descent of the aircraft as a function of the rate of sink and the reachable distance.