Abstract: A power distribution control approach employs power distribution buses that are controllably energized and de-energized to control which aerial vehicle systems received power based on the applicable operational mode. A method of controlling power distribution in an electrically powered vertical takeoff and landing aircraft includes receiving an operational mode indication that identifies an operational mode. The operational mode is one of predetermined operational modes for the aircraft. Power distribution buses of the aircraft are controlled, based on the operational mode indication, to control each of the power distribution buses to be energized or de-energized.

Abstract: Power distribution systems, battery packs, and batteries employ battery modules that are connected in series to generate a high-voltage output and in parallel to generate a low-voltage output. A battery includes battery modules and a direct current to direct current converter. The battery modules are electrically connected in series to generate a first battery high-voltage output. The battery modules are electrically connected in parallel to generate a battery modules low-voltage output. The direct current to direct current converter generates a battery low-voltage output from the battery modules low-voltage output.

Abstract: Electrically powered vehicles with redundant power distribution circuits employ inverters and a multi-phase alternating current (AC) motor. An electrically powered vehicle includes batteries, inverters, interphase transformers, and a three-phase AC motor. Each of the inverters generates a three-phase AC input from power supplied by an associated one of the batteries. The interphase transformers generate drive phases for the AC motor from the three-phase AC inputs generated by the inverters.

Abstract: A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of power distribution circuits each couple a battery of the plurality of batteries to two or more electric propulsion systems. The plurality of electric propulsion systems are positioned on the aircraft to apply balanced forces to the aircraft such that in the event of a failure, the aircraft remains stable and only experiences a loss in altitude or speed.

Abstract: An electrically powered vehicle includes a plurality of batteries and a plurality of DC to DC converters, each coupled to a respective battery of the plurality of batteries. Each DC to DC converter transfers power from a respective battery to a common DC bus. The common DC bus is coupled to a plurality of inverter circuits that convert the DC power to AC power. A plurality of electric motors receive power from the plurality of inverter circuits to propel the vehicle. During a regenerative event, the DC to DC converters can transfer power from the motors back to the batteries. In response to the failure of a battery, the DC to DC converters can isolate the remainder of the system from the failure.

Abstract: Embodiments of cooling a motor controlling using a motor are disclosed. In some embodiments, a system includes an electric motor including at least one rotor with integrated features positioned and configured to pull air into and through the electric motor. The system also includes at least one motor controller each comprising a heat sink positioned in an air intake path from a source of air to the electric motor. A method of manufacturing the system includes arranging at least one motor controller and at least one electric motor, coupling the at least one motor controller and at least one electric motor via a flexible duct, and adapting the arrangement of the at least one motor controller and the at least one electric motor to passively provide cooling via airflow through the at least one motor controller and at least one electric motor in proportion to a load on the at least one electric motor.

Abstract: An electrically powered vehicle includes a plurality of batteries and a plurality of DC to DC converters, each coupled to a respective battery of the plurality of batteries. Each DC to DC converter transfers power from a respective battery to a common DC bus. The common DC bus is coupled to a plurality of inverter circuits that convert the DC power to AC power. A plurality of electric motors receive power from the plurality of inverter circuits to propel the vehicle. During a regenerative event, the DC to DC converters can transfer power from the motors back to the batteries. In response to the failure of a battery, the DC to DC converters can isolate the remainder of the system from the failure.

Abstract: Embodiments of cooling a motor controlling using a motor are disclosed. In some embodiments, a system includes an electric motor including at least one rotor with integrated features positioned and configured to pull air into and through the electric motor. The system also includes at least one motor controller each comprising a heat sink positioned in an air intake path from a source of air to the electric motor. A method of manufacturing the system includes arranging at least one motor controller and at least one electric motor, coupling the at least one motor controller and at least one electric motor via a flexible duct, and adapting the arrangement of the at least one motor controller and the at least one electric motor to passively provide cooling via airflow through the at least one motor controller and at least one electric motor in proportion to a load on the at least one electric motor.