An electric aircraft includes rotors for providing lift for vertical take-off and landing of the aircraft, proprotors that are tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft, a first battery pack for powering a first rotor and a first proprotor, a second battery pack for powering a second rotor and a second proprotor, a first electric power bus electrically connecting the first battery pack to the first rotor and proprotor, and a second electric power bus electrically connecting the second battery pack to the second rotor and proprotor, wherein the second electric power bus is electrically isolated from the first electric power bus.

The disclosure relates to an electrical power system for providing a stabilised DC voltage to a power bus. Example embodiments include an electrical power system comprising: a DC power bus having first and second DC power bus terminals; an electrical storage unit having first and second terminals, the second terminal connected to the second DC power bus terminal; a DC:DC converter having first and second DC:AC converters and a transformer connected between the first and second DC:AC converters, the first DC:AC converter connected between the first terminal of the electrical storage unit and the first DC power bus terminal; and a controller connected to control a switching operation of one or both of the first and second DC:AC converters.

A system for charging an electric aircraft. The system includes an electric aircraft port, at least a current conductor, a power supply circuit and a controller. The electric aircraft port is configured to mate with a charging connector. At least a portion of the at least a current conductor is at the electric aircraft port. The at least a current conductor is configured to conduct a charging current to at least an energy source of the electric aircraft. The power supply circuit is electrically connected to the at least a current conductor. The power supply circuit is configured to regulate the charging current supplied to the at least an energy source. The controller is communicatively connected to the power supply circuit. The controller is configured to control operation of the power supply circuit as a function of a power threshold. A method for charging an electric aircraft is also provided.

An electric power supply system for an aircraft includes: a first electric source and a second electric source coupled together to supply electric power to a set of electrical loads, and a controller configured to acquire a piece of information on the current electric consumption consumed by the set of electrical loads; acquire a piece of information corresponding to a target ratio of the distribution, between the first and second electric sources, of the current electric consumption consumed by the set of electrical loads; perform frequency filtering of the current electric consumption to determine a transient consumption portion of the current electric consumption; determine control setpoints for the first electric source and for the second electric source in accordance with the target distribution ratio and with the transient consumption portion; and apply the control setpoints to the first and second electric sources.

The disclosure is directed to methods and systems for provisioning mobile electric vehicles with various operational settings data transmitted over the air. A vehicle or its components may operate according to operational settings corresponding to operational settings data included in the vehicle components. A server that is remote to the vehicle may comprise operational settings data and may transmit operational settings data to the vehicle. The server may transmit operational settings data automatically, such as on a periodic basis, in response to a request, such as from a user or from a vehicle component or anytime new or updated operational settings data are available for the vehicle or its components.

A power supply system includes a set of power supply units, each power supply unit arranged electrically in series and defining a common power supply, each power supply unit having a power module and a selective bypass for selectively bypassing the respective power module. The power supply system can meet a power demand.

Aircraft electric power distribution systems and methods of operating aircraft electrical power distribution systems are provided. One such method comprises determining a measure of an electrical power demand of a power and propulsion system of the aircraft; setting a target operating voltage of the aircraft electrical power distribution system based at least in part on the measure of the electrical power demand; and controlling the operating voltage in accordance with the set target operating voltage. In some embodiments the measure of the electrical power is a measure of an operating parameter of a gas turbine engine or propulsor of the aircraft.

Various arrangements for recharging an energy source are provided herein. In response to a device having a state of charge below a first threshold, a mobile device, such as an unmanned aerial vehicle (UAV) can be provided location information for the device. The mobile device may travel to within a certain proximity from the device. The mobile device may then a connection with the device. A charging sequence may then be initiated to recharge the energy source of the device.

A system for battery management for electric aircraft batteries includes an energy storage system configured to provide energy to the electric aircraft via a power supply connection, the energy storage system including: a battery pack, a sensor configured to detect a condition parameter of the battery pack and generate a battery datum based on the condition parameter, a pack monitoring unit (PMU) configured to receive the battery datum, and a high voltage disconnect configured to terminate the power supply connection between the battery pack and the electric aircraft; a high voltage bus electrically connected to the high voltage disconnect; a primary functional display configured to display information based on battery datum; and a first controller area network (CAN) bus and a second CAN bus communicatively connected to the PMU, the high voltage bus, and the primary functional display.

A system for retrofitting a wall of an aircraft monument includes a modular power charging unit and mounting hardware. The modular power charging unit includes a housing containing an electrical port component, a cable harness, and a switch. The housing has a plurality of screw holes and a back panel having an opening through which the cable harness extends. The mounting hardware includes a plurality of threaded inserts, each configured to be inserted into one of a plurality of mounting holes formed in the wall, and a plurality of screws, each configured to extend through a screw hole of the housing and into a threaded insert. The housing is configured to be secured to a first side of the wall so that the entirety of the housing projects outward from the first side and only the cable harness extends through a cable-harness hole formed through a thickness of the wall.