Power distribution system and method for an aircraft

A method of distributing power to aircraft systems of an aircraft, the aircraft having a plurality of rotor assemblies and one or more flight control computers configured to provide operation of the plurality of rotor assemblies, the method comprising:

• distributing power to a first rotor assembly and a fourth rotor assembly of the plurality of rotor assemblies from a first battery and a first power distribution unit, the first rotor assembly and the fourth rotor assembly are outer front rotor assemblies of the aircraft;
• distributing power to a second rotor assembly of the plurality of rotor assemblies from a second battery and a second power distribution unit, the second rotor assembly is an inboard front rotor assembly;
• distributing power to a third rotor assembly of the plurality of rotor assemblies from a third battery with a third power distribution unit, the third rotor assembly is another inboard front rotor assembly;
• and
• distributing power to the first rotor assembly and the fourth rotor assembly from a fourth battery with a fourth power distribution unit;
• wherein the second rotor assembly only receives power from the second battery and the third rotor assembly only receives power from the third battery;
• and
• wherein the first, second, third, and fourth power distribution units are implemented with consideration of possible failure modes of any of the batteries and any of the power distribution units such that controlled flight is maintained despite failure of any one of the batteries or any one of the power distribution units, controlled flight being maintained without implementation of additional power units outside of the first, second, third, and fourth batteries.

A power distribution system for an aircraft, comprising:

• the aircraft having six dual motor rotor assemblies and one or more flight control computers configured to provide operation of the six dual motor rotor assemblies;
• a plurality of batteries providing power to the six dual motor rotor assemblies, the plurality of batteries consisting of:
• a first battery providing power to a first rotor assembly, a fourth rotor assembly, and a fifth rotor assembly, the first rotor assembly being a left outer front rotor assembly, the fourth rotor assembly being a right outer front rotor assembly, and the fifth rotor assembly being a left side rotor assembly;
• a second battery providing power to a second rotor assembly and a sixth rotor assembly, the second rotor assembly being a left inboard front rotor assembly and the sixth rotor assembly being a right side rotor assembly;
• a third battery providing power to a third rotor assembly and the fifth rotor assembly, the third rotor assembly being a right inboard front rotor assembly;
• and
• a fourth battery providing power to the first rotor assembly, the fourth rotor assembly, and the sixth rotor assembly;
• wherein the second rotor assembly only receives power from the second battery and the third rotor assembly only receives power from the third battery;
• and
• wherein the plurality of batteries are implemented with consideration of possible failure modes of any of the batteries such that controlled flight is maintained despite failure of any one of the batteries, controlled flight being maintained without implementation of additional power units outside of the plurality of batteries.