A system and method for the overcurrent protection in an electric vehicle is illustrated. The system comprises an AC pin, a DC pin, an electric vehicle charging connector, wherein the electric vehicle charging connector comprises a protection circuit, wherein the protection circuit is configured to control a transmission of power through the electric vehicle charging connector, a sensor, wherein the sensor is configured to detect an output current, and a controller communicatively connected to the sensor. The controller is configured to detect an overcurrent output as a function of the output current and trip the protection circuit as a function of the overcurrent output.

The invention relates to a hybrid propulsion architecture (100) for an aircraft, comprising: —a first source (102) of a first energy type, —second sources (104) of a second energy type different from the first energy type, —electrical propulsion systems (106), —an electric power supply network (118) connecting the first and second sources (102, 104) to the electrical propulsion systems, such that each electrical propulsion system is powered by the first source and by one of the second sources, the architecture being characterised in that it further comprises: —means for segregating (120) the electrical propulsion systems, which means are arranged in the electric power supply network and configured to impose a direction of flow of the electric power from the first source to the electrical propulsion systems.

Electrical power supply system having a DC distribution bus; a rechargeable battery module which delivers DC power to the DC distribution bus in a discharge mode, and absorbs DC power from the DC distribution bus in a recharge mode; a DC/DC converter comprising an inductor and plural switches, the DC/DC converter being connected between the DC distribution bus and the rechargeable battery module; and a heat transfer arrangement configured to transfer heat between the DC/DC converter and the rechargeable battery module. The module has an idling mode of operation in which it neither delivers nor absorbs DC power to/from DC distribution bus, wherein the converter is repeatedly switchable between (i) a ramping-up configuration in which a current is withdrawn from a source, and (ii) a freewheeling configuration in which the current from the ramping-up configuration is isolated from the source to flow in a continuous loop within the converter.

A battery management system integrated in a battery pack configured for use in electric aircraft, the system comprising a first battery management component comprising a first sensor suite configured to measure a first plurality of battery pack data. The battery management system comprising a second battery management component comprising a second sensor suite configured to measure a second plurality of battery pack data. The battery management system comprising a data storage system configured to store the first plurality of battery pack data and the second plurality of battery pack data.

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.

A system of a machine includes a network of a plurality of nodes distributed throughout the machine, a controller, and a power extraction system within at least one of the nodes. Each of the nodes is operable to communicate through one or more radio frequencies. The controller is configured to communicate with the network of nodes by transmitting the one or more radio frequencies through one or more waveguides. The power extraction system is configured to extract power from the one or more radio frequencies as a first power source, extract power from a second power source, and provide power to one or more components of the system based on power extracted from either or both of the first power source and the second power source.

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.

The presently disclosed embodiments generally relate to systems, devices, and methods for sensing and charging of electronic devices using coils. In some embodiments, the presently disclosed system can include a pad, a charging foot, and a backpack. The pad can include one or more nested coils therein that can sense one or more corresponding receiver coils of an unmanned aerial vehicles (UAV) that landed thereon. The nested coils of the pad can provide charging energy to the UAV independent of the location along the pad in which the UAV landed, and no precise alignment between the receiver coils and the charging coils is required. The charging foot can be attached to one or more legs of the UAV, and can include a receiver coil and circuitry to regulate energy received by the coil to a charging voltage level that can be provided to the battery.

A system for restricting power to a load to prevent engaging a circuit protection device for an electric aircraft includes an energy source. The energy source is communicatively coupled to a load, wherein the load includes a portion of a propulsion system. The system includes sensors configured to sense an electrical parameter. The system includes an aircraft controller communicatively connected to the energy source, wherein the aircraft controller is configured to receive an electrical parameter, compare the electrical parameter to a current allocation threshold, detect that the electrical parameter has reached a current allocation threshold, generate a current allocation threshold notification as a function of the detection, wherein the current allocation threshold notification indicates that the electrical parameter has reached the current allocation threshold.

An example system includes a first plurality of nacelles located on a first side of an aircraft, wherein each nacelle of the first plurality of nacelles includes an electric motor coupled to a propulsor, wherein an outboard nacelle of the first plurality of nacelles includes an electrical energy storage system (ESS) coupled to a first electrical bus; and a second plurality of nacelles located on a second side of the aircraft, wherein each nacelle of the second plurality of nacelles includes an electric motor coupled to a propulsor, wherein an outboard nacelle of the second plurality of nacelles includes an ESS coupled to a second electrical bus.