Abstract: A system for a rotor with directional magnetic field configured for use in electric aircraft motor that includes a magnet array having an outer cylindrical surface, an inner cylindrical surface, an upper edge, and a lower edge, which further includes a plurality of magnets, where the plurality of magnets is configured to create a directional magnet field and an electrically insulating epoxy, where the electrically insulating epoxy envelops at least a portion of the plurality of magnets.

Abstract: An electric vehicle charging connector including a charging connector. The charging connector including a direct current pin and an alternating current pin. The electric vehicle charging connector also including a coupling mechanism configured to: couple the charging connector to an electric vehicle, enable a flow of electricity from the charging connector to the electric vehicle, and disable the flow of electricity from the charging connector to the electric vehicle.

Abstract: The present invention is a system and methods for an immediate shutdown of an electric vehicle charger. The system may include a sensor, which is communicatively connected to a charging connection, and a control circuit, which is communicatively connected to the sensor. If a disruption element is determined by the control circuit as a function of a charging datum of the sensor, then control circuit is configured to conduct an immediate shutdown of charger by disabling a communication of a charging connection to prevent harm to an electric vehicle, a charger, and/or a user.

Abstract: The present invention is a system and methods for an immediate shutdown of charging for an electric vehicle charger. The system may include a sensor, which is communicatively connected to a charging connection, and a control circuit, which is communicatively connected to the sensor. If a disruption element is determined by the control circuit as a function of a charging datum of the sensor, then control circuit is configured to conduct an immediate shutdown of charger by disabling a communication of a charging connection to prevent harm to an electric vehicle, a charger, and/or a user.

Abstract: A connector with overvoltage protection, and methods of use, for charging an electric aircraft. The connector includes a housing, at least a current conductor, a protection circuit, at least a sensor and a controller. The housing is configured to mate with an electric aircraft port of the electric aircraft. The at least a current conductor is configured to conduct a current. The protection circuit is configured to control transmission of electrical power through the connector. The at least a sensor is configured to detect an output voltage of the connector. The controller is communicatively connected to the at least a sensor. The controller is configured to determine an overvoltage output as a function of the output voltage, and activate the protection circuit based on detection of the overvoltage output.

Abstract: A system with a safety feature for charging an electric aircraft. The system includes an electric aircraft port of an electric aircraft, a sensor on the electric aircraft, and a computing device communicatively connected to the electric aircraft port and the sensor. The electric aircraft port is configured to mate with a charging connector. The sensor is configured to detect a sensor datum of the charging connector. The computing device is configured to receive the sensor datum, generate a charging instruction set as a function of the sensor datum, transmit the charging instruction set to the electric aircraft port, and enable charging of the electric aircraft, by the charging connector and through the electric aircraft port, as a function of the charging instruction set. The charging instruction set includes a safety lock instruction. A method with a safety feature for charging an electric aircraft is also provided.

Abstract: A system for a safety feature for charging an electric aircraft is presented. The system includes a sensor, wherein the sensor is configured to detect a sensor datum from an electric aircraft. The system further includes a computing device, wherein the computing device is configured to receive the sensor datum, authenticate the electric aircraft, generate a charging instruction set as a function of the sensor datum, wherein the charging instruction set comprises a safety lock instruction, and transmit the charging instruction set to a charging connector. The system further includes a charging connector, wherein the charging connector is configured to connect to an electric aircraft port of the electric aircraft and perform the charging instruction set on the electric aircraft set as a function of the electric aircraft port.

Abstract: A system for emergency shutdown of an electric aircraft port in response to a disconnection is presented. The system includes a computing device, wherein the computing device is configured to receive a sensor datum from a sensor, determine a disruption element between a charging connector and an electric aircraft port as a function of the sensor datum, and initiate a disconnection protocol as a function of the disruption element.

Abstract: A system for managing residual energy for an electric aircraft, wherein the system includes a battery pack incorporated in the electric aircraft, wherein the battery pack includes a plurality of battery modules and at least a pack monitor unit configured to generate a battery pack datum. The system further includes a charging component connected to the battery pack and a sensor connected to the charging component and configured to detect at least an electrical parameter of the charging component and the electric aircraft and generate a residual datum as a function of the at least an electrical parameter and the battery pack datum. The system further includes a computing device configured to receive the residual datum from the sensor, identify a residual element, generate an alert datum as a function of the residual element, and execute a security measure as a function of the alert datum.

Abstract: A system for managing residual energy for an electric aircraft, wherein the system includes a battery pack incorporated in the electric aircraft, wherein the battery pack includes a plurality of battery modules and at least a pack monitor unit configured to generate a battery pack datum. The system further includes a charging component connected to the battery pack and a sensor connected to the charging component and configured to detect at least an electrical parameter of the charging component and the electric aircraft and generate a residual datum as a function of the at least an electrical parameter and the battery pack datum. The system further includes a computing device configured to receive the residual datum from the sensor, identify a residual element, generate an alert datum as a function of the residual element, and execute a security measure as a function of the alert datum.

Abstract: A system for a battery with spring conductors is illustrated. The system comprises a case, a plurality of battery cells, and a lid. The case is coupled to the aircraft and comprises a thermal conducting interior surface. The plurality of battery cells are inserted into the case in layers and comprises a thermally conducting fin contacting the thermally conducting interior surface, a pouch cell, and a vent configured to vent ejecta from the pouch cell. The pouch cell comprises a pair of electrodes, a pair of foil tabs electrically connected to the electrodes, an insulator layer located between the pair of foil tabs, a pouch encompassing the pair of foil tabs and the insulation layer, and an electrolyte within the pouch. The lid is configured to interact with the case.

Abstract: In an aspect, a system for recharging an electric vehicle. A system includes a recharging component. A recharging component includes a ventilation system. A system includes a sensor configured to detect a plurality of data from the recharging component. A sensor is configured to generate an environment datum as a function of the plurality of data. A system includes a control pilot. A control pilot is in electronic communication with a sensor. A control pilots is configured to receive an environment datum from a sensor. A control pilot is configured to generate a ventilation requirement datum from an environment datum. A control pilot is configured to command a recharging component to perform a ventilation process. A system includes a pilot display. A pilot display is coupled to an electric vehicle. A pilot display is configured to display a ventilation requirement datum to a pilot.

Abstract: A system for overvoltage protection in an electric aircraft, and a method for its use. The system includes an energy storage element, an overvoltage protection device, a ground conductor, at least a current conductor, at least a sensor, and a controller. The overvoltage protection device is configured to control transmission of electrical power through the connector. The at least a sensor is configured to detect an output voltage of the connector. The controller is communicatively connected to the at least a sensor. The controller is configured to determine an overvoltage output, and activate the over based on detection of the overvoltage output.

Abstract: A system for pre-charging short circuit detection in electric aircraft. The system includes a charging connector and a controller communicatively connected to the charging connector. The charging connector includes a housing, at least a conductor, and at least a control signal conductor. The housing is configured to mate with an electric aircraft port of an electric aircraft. The at least a conductor is configured to conduct a charging current to the electric aircraft. The at least a control signal conductor is configured to conduct a control signal. The controller is configured to receive a circuit health datum, through the at least a control signal conductor, prior to initiation of charging of the electric aircraft, and to disable initiation of charging of the electric aircraft if the circuit health datum comprises a short circuit datum. A method for pre-charging short circuit detection in electric aircraft is also provided.

Abstract: A connector with overvoltage protection, and methods of use, for charging an electric aircraft. The connector includes a housing, at least a current conductor, a protection circuit, at least a sensor and a controller. The housing is configured to mate with an electric aircraft port of the electric aircraft. The at least a current conductor is configured to conduct a current. The protection circuit is configured to control transmission of electrical power through the connector. The at least a sensor is configured to detect an output voltage of the connector. The controller is communicatively connected to the at least a sensor. The controller is configured to determine an overvoltage output as a function of the output voltage, and activate the protection circuit based on detection of the overvoltage output.

Abstract: Various techniques are provided to assemble, manufacture, and use a power source. A power source assembly system is provided to apply a compressive force on a plurality of battery cells so that the battery cells may be inserted into a compact container without damaging the battery cells.

Abstract: In an aspect, a system for recharging an electric vehicle. A system includes a recharging component configured to deliver power to an energy source of an electric vehicle. A recharging component includes a sensor. A sensor is configured to measure data of a recharging component. A system includes a charging database in electronic communication with a sensor. A charging database is configured to receive data of a recharging component. A system includes a computing device coupled to a recharging component. A computing device is configured to retrieve data from a charging database. A computing device is configured to monitor data form a charging database. A computing device is configured to display data from a charging database.

Abstract: A system for emergency shutdown of an electric charger in response to a disconnection is presented. The system includes a computing device, wherein the computing device is configured to receive a sensor datum from a sensor, determine a disruption element between a charging connector and an electric vehicle as a function of the sensor datum, and initiate a disconnection protocol as a function of the disruption element.

Abstract: A system for establishing an ambient requirement in an electric aircraft. The system includes an electric aircraft port on the electric aircraft, wherein the electric aircraft port is configured to removably mate to a charging connecter, and wherein the electric aircraft port includes: a sensor configured to generate a datum of a battery of the electric aircraft; a controller communicatively connected to the sensor, wherein the controller is configured to: receive the datum from the sensor; determine, as a function of the datum, an ambient requirement for the battery; and transmit the ambient requirement for implementation.

Abstract: An electric charging and metering device, including a charging connector, the charging connector configured to connect a charger to an electric aircraft; a sensor; and a processor. The charging connector including a direct current pin and an alternating current pin. The sensor communicatively connected to the charging connector. Additionally, the sensor configured to: monitor the direct current pin and the alternating current pin; measure an energy datum, the energy datum relating to a property of the charger, the charging connector electrically connected to the charger; and transmit the energy datum to a processor. The processor configured to receive the energy datum and calculate an electricity usage of the charger.