Systems and methods for power distribution in electric aircraft

An electric aircraft, comprising:

• a fuselage;
• a plurality of first electric propulsion units arranged on opposite sides of the fuselage and a plurality of second electric propulsion units arranged on opposite sides of the fuselage, wherein the plurality of first electric propulsion units is configured to be aft of the plurality of second electric propulsion units during forward flight;
• and
• a plurality of battery packs, wherein:
• a first battery pack of the plurality of the battery packs is configured to provide power to a first portion of one of the first electric propulsion units on one side of the fuselage and provide power to a first portion of one of the second electric propulsion units on the other side of the fuselage, and
• a second battery pack of the plurality of battery packs is configured to:
• provide power to a second portion of the one of the first electric propulsion units,
• provide power to a second portion of the one of the second electric propulsion units on the other side of the fuselage, and
• after a failure of the first battery pack, continue to provide power to the second portion of the one of the first electric propulsion units and to the second portion of the one of the second electric propulsion units.