The present disclosure describes at least a coupling circuit for powering an electric or hybrid aircraft with an output voltage. The couple circuit can include multiple connecting inputs, a charging interface, a connecting output, a high-power diodes arrangement, and a pre-charge circuit. The multiple connecting inputs can connect multiple battery packs. The charging interface can connect to a charger for charging the multiple battery packs. The connecting output can connect with a hardware controller. The high-power diodes arrangement can electrically connect to each respective connecting input and the charging interface. The high-power arrangement can include for each battery pack a first high-power diode and a second high-power diode. The pre-charge circuit can electrically connect to the high-power diode arrangement. The pre-charge circuit can include a first branch with a first switch, and a second branch in parallel with the first branch.

The present disclosure relates to an in-place alignment method for wireless charging of an urban air mobility and a device and a system therefor. A wireless charging method includes acquiring location information of a supply device for supplying wireless power, moving an urban air mobility to the supply device based on the location information, performing pairing with a user equipment (UE) based on a distance from the urban air mobility to the supply device, aligning a wireless power receiving pad of the urban air mobility and a wireless power transmitting pad of the supply device based on a control signal of the paired UE, and charging a battery of the urban air mobility by receiving wireless power from the supply device. The present disclosure maximizes a wireless charging efficiency and minimizes a power waste by quickly and accurately aligning pads of the urban air mobility and the supply device.

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 battery management and monitoring system integrated in a battery pack configured for use in electric aircraft. The system includes a sensor suite configured to measure a plurality of battery pack data. The system includes a battery monitoring component configured to detect a first fault in the battery pack and produce a first fault detection response notifying a user of the first fault in the battery pack. The system includes a battery management component configured to detect a second fault in the battery pack and produce a second fault detection response configured to mitigate the second fault in the battery pack. The system includes an interlock component having a first mode and a second mode, configured to enable the battery monitoring component and disable the battery management component when in the first mode and enable the battery management component and disable the battery monitoring component when in the second mode.

System and method for allocating load power drawn from multiple batteries for powering propulsion of a vehicle. The system includes: high-energy and high-power batteries respectively designed for optimal production of DC power during high-specific-energy and high-specific-power propulsion; and battery health management systems configured to monitor state of charge and state of health of the batteries and generate battery status signals. The system further includes a propulsion load configured to produce propulsion force using power converted from power generated by at least one of the batteries and a system controller configured to allocate load power drawn from the high-energy and high-power batteries for use by the propulsion load in dependence on a propulsion phase of the vehicle and the battery status.

An electrical power distribution system for converting and distributing electrical power to local loads within a vehicle is disclosed. The electrical power distribution system includes at least one generator providing high voltage AC (HVAC) power, a primary power panel for receiving the HVAC power from the generator, and a plurality of distribution conversion units located throughout the vehicle. The plurality of distribution conversion units convert the HVAC power from the primary power panel into medium voltage AC (MVAC) power and low voltage DC (LVDC) power for consumption by the local loads within the vehicle. The electrical power distribution system also includes a plurality of HVAC distribution feeder lines. Each HVAC distribution feeder line connects the primary power panel to one of the plurality of distribution conversion units.

A power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, a power management device coupled to the first power supply bus bar, at least one primary electrical equipment including a primary load being coupled in parallel to the power management device, and at least one secondary electrical equipment including a secondary load being coupled in parallel to the power management device. The power manager device is configured to supply electrical power to the at least one secondary electrical equipment, to supply electrical power to the at least one primary electrical equipment, and to deactivate the power supply to the at least one secondary electrical equipment, as long as the at least one primary electrical equipment is supplied with electrical power.

Electrical distribution system for an aircraft comprising at least one electrical supply path comprising at least one power unit capable of opening or closing the connection between at least one electrical energy source and at least one device of the aircraft. The system comprises protection cards (2b, 2n) each comprising at least two microcontrollers each capable of sending a command to each power unit of the electrical supply paths protected by each protection card and, among the set of microcontrollers of the protection cards, at least two microcontrollers are provided with a communication and computation function with all of the microcontrollers of the protection cards (2b, 2n).

An aerial platform receives power in the form of light, for example laser light, transmitted via an optical fiber from a remote optical power source. The platform comprises a receiver which converts at least a portion of the light to a different form of power, for example electric power. The platform also comprises a propulsion element which consumes the different form of power to generate propulsive thrust. Supplying power to the aerial platform from a remote source enables the platform to remain aloft longer than a battery or fuel tank carried by the platform would allow. Transmitting the power in the form of light is preferable in many cases to transmitting electric power, because electrical conductors are generally heavier than optical fibers, and are hazardous in the presence of lightning or a high-voltage power line.

A harmonics correction circuit is implemented as an independent device (such as a SiP or ASIC), and includes (1) a first node, (2) a second node, (3) a first current path extending from the first node to the second node, (4) a second current extending from the first node to ground, (5) a third current path extending from the first node to the second node, (6) a sense resistor electrically connected to the second node and to ground, (7) a differential circuit (e.g., a differential amplifier or other type of operational amplifier (“op-amp”)) that has a first input, a second input, and an output, (8) a transistor comprising a gate that is electrically connected to the output of the differential circuit, a drain that is electrically connected to the third current path, and a source that is electrically connected along the third current path.