US Patent 11465532 Systems and methods for power distribution in electric aircraft

A power distribution system for an electric aircraft includes a first electric propulsion unit comprising at least two power stages; a first battery pack electrically connected to a first power stage of the at least two power stages; a second battery pack electrically connected to a second power stage of the at least two power stages; and a control system configured to control the first battery pack, the second battery pack, the first power stage, and the second power stage to transfer power from the first battery pack to the second battery pack through the first power stage and the second power stage.