Electrical power supply device for aircraft with electric propulsion

An electric power supply device for an electric aircraft, comprising:

• first and second electric motor configured to propel the electric aircraft;
• first and second high-voltage electric circuits connected respectively to the first and second electric motors;
• a low-voltage electric circuit connected to at least one of a command member and a control member of the electric aircraft;
• first and second battery packs connected respectively to the first and second high-voltage electric circuits;
• first and second battery management systems connected to the low-voltage circuit, the first and second battery management systems connected respectively to the first and second battery packs;
• and
• a first electric converter connected to the first high-voltage electric circuit and to the low-voltage electric circuit.

A method of starting an electric aircraft comprising an electric power supply device, comprising the steps of:

• wherein the electric power device comprises:
• first and second electric motor configured to propel the electric aircraft, first and second high-voltage electric circuits connected respectively to the first and second electric motors;
• a low-voltage electric circuit connected to at least one of a command member and a control member of the electric aircraft;
• first and second battery packs connected respectively to the first and second high-voltage electric circuits;
• first and second battery management systems connected to the low-voltage circuit, the first and second battery management systems connected respectively to the first and second battery packs;
• a first electric converter connected to the first high-voltage electric circuit and to the low-voltage electric circuit;
• and a backup battery connected to the first battery management system via a switch, the backup battery is configured to deliver a current sufficient to bring the electric power supply device into operation;
• closing the switch to connect the backup battery to the first battery management system;
• checking a voltage of the backup battery utilizing the first battery management system and interrupting a start of the electric aircraft in response to a determination that the voltage of the backup battery is below a critical threshold;
• pre-charging of first and second voltage inverters, each voltage converter is configured to convert a high-voltage DC voltage into a three-phase AC supply by chopping, and each voltage inverter is connected between a high-voltage electric circuit and its respective electric motor;
• closing of a contact switch of each battery pack;
• initiating an operation of the electric converter;
• checking a voltage of at least one battery pack using a corresponding battery management system and interrupting the start of the electric aircraft in response to a determination that the voltage of said at least one battery pack is below the critical threshold;
• and
• opening the switch to disconnect the backup battery.