Abstract: A system for swarm communication for an electric aircraft fleet, wherein the system includes a plurality of electric aircrafts connected by a mesh network. The system further includes a computing device communicatively connected to the mesh network, wherein the computing device includes an authentication module configured to authenticate each electric aircraft and facilitate communication of a plurality of aircraft data between the plurality of electric aircrafts. The computing device includes a plurality of communication components, each assigned to an electric aircraft of the electric aircraft fleet, wherein each communication component is configured to transmit the aircraft data to the communication component of its assigned electric aircraft. The system further includes a cloud database configured to record the plurality of aircraft data.

Abstract: A proximity detection system for facilitating charging of electric aircraft. The proximity detection system includes at least a computing device. The at least a computing device is configured to receive a detection datum from at least a sensor, determine a proximal element as a function of the detection datum, and communicate a notification as a function of the proximal element to at least one of the electric aircraft and a charging structure. The detection datum includes information on at least one of the electric aircraft and the charging structure. The proximal element includes information on a spacing between the electric aircraft and the charging structure. A proximity detection method for facilitating charging of an electric aircraft is also provided.

Abstract: A system for disabling an electric vehicle during charging, including an energy storage device, the energy storage device attached to an electric vehicle. T The system including a charging port, wherein the charging port is configured to engage with a charging connector, the charging port disposed on the electric vehicle and electrically connected to the energy storage device. The system also including a presence sensor, the presence sensor communicatively connected to the charging port, the presence sensor configured to detect whether the charging connector is engaged with the charging port. Additionally, the system including an interlock component, the interlock component configured to disable the electric vehicle when the charging connector is engaged with the charging port.

Abstract: Aspects relate to a connector for charging an electric vehicle and a method for its use. An exemplary connector includes at least a direct current conductor configured to conduct a direct current, at least an alternating current conductor, configured to conduct an alternating current, at least a computing device wherein the computer is configured to receive a measurement datum of a battery module from a communicatively connected sensor, determine an operating condition of the charging circuit; identify an error element as a function of the operating condition, and transmit the identification of the error element to a data storage system.

Abstract: A system and method for the overcurrent protection in an electric vehicle is illustrated. The system comprises an electric vehicle charging port that includes an AC pin, a DC pin, a sensor, and a controller. The electric vehicle charging port also includes a protection circuit, wherein the protection circuit is configured to control a transmission of power through the electric vehicle charging port.

Abstract: An electric vehicle charging connector, including a set of pins, a sensor, and a controller. The set of pins may include a DC pin, wherein the DC pin is configured to supply DC power to a charging port, wherein the charging port comprises a locking mechanism. The sensor can detect power flow from the pins to the charging port. The controller is communicatively connected to the sensor and configured to receive a signal from the sensor and send a locking signal to a locking mechanism. The locking mechanism comprises an engaged state wherein the charging connector is mechanically coupled to the charging port and a disengaged state wherein the charging connector is mechanically uncoupled form the charging port, wherein the locking mechanism is configured to receive a locking signal from the controller of the charging connector and enter the engaged state.

Abstract: Aspects relate to a charging port of an electric aircraft and methods of use terminating a charging connection between a charger and the electric aircraft. A charging port includes a controller that is configured to receive a control signal from a remote device and terminate the charging connection in response to the control signal.

Abstract: A system and method for the overcurrent protection in an electric vehicle is illustrated. The system comprises an electric vehicle charging port that includes an AC pin, a DC pin, a sensor, and a controller. The electric vehicle charging port also includes a protection circuit, wherein the protection circuit is configured to control a transmission of power through the electric vehicle charging port.

Abstract: Aspects relate to a connector of a charger and methods of use terminating a charging connection between the charger and an electric aircraft. A connector includes a controller that is configured to receive a control signal from a remote device and terminate the charging connection in response to the control signal.

Abstract: Aspects relate to a charger for an electric aircraft with failure monitoring and method for its use. An exemplary charger for an electric aircraft with failure monitoring includes a charging circuit. Included within the charging circuit is a connector configured to mate with an electric aircraft port of an electric aircraft and at least a current conductor configured to conduct a current. At least a conductor comprises a direct current conductor configured to conduct a direct current. A charger may include a control circuit configured to command the charging circuit of an electric aircraft as a function of charging datum. A charger may also include a failure monitor circuit, the failure monitor circuit configured to initiate a failure mitigation procedure as a function of a failure of the charging circuit.

Abstract: A charging system for mitigating charging failure for an electric aircraft, the system comprising a charger port located on the electric aircraft and configured to mate with a charging connector, a sensor communicatively connected to the charger port and configured to detect a charging datum, and a controller communicatively connected to the charger port and the sensor. The controller is configured to receive charging datum from the sensor, detect a charging failure as a function of a comparison between the charging datum to a pre-set charging datum threshold, and record the charging failure in a database.

Abstract: A selectively deployable heated propulsor system which may be integrated into vehicles, airplanes, or any other machinery configured for flight. The system includes a structural feature that includes a mounted propulsor including a rotor and a motor mechanically coupled to the rotor allowing the rotor to rotate when in an activated mode. The mounted propulsor includes a chamber configured to support a first configuration where the propulsor and the rotor are stowed and heated in an enclosed environment, and a second configuration where the rotor is deployed.

Abstract: A system for a connector for charging an electric aircraft, wherein the system comprises a charging port located on an electric aircraft, wherein the charging port is configured to mate with a charger connector, receive at least an electrical current from current conductor, and detect a detection datum using at least a sensor. The system also includes a controller communicatively connected to the charging port, wherein the controller is configured to receive the detection datum from the at least a sensor and stop flow of the electrical current as a function of the detection datum.

Abstract: Aspects relate to a connector and methods of use for charging an electric vehicle. An exemplary connector includes a housing configured to mate with an electric vehicle port of an electric vehicle, where the housing includes a fastener for removable attachment with the electric vehicle port, at least a direct current conductor configured to conduct a direct current, at least an alternating current conductor, configured to conduct an alternating current, at least a control signal conductor configured to conduct a control signal, at least a ground conductor configured to conduct to a ground, at least a coolant flow path configured to contain a flow of a coolant, and at least a proximity signal conductor configured to conduct a proximity signal indicative of attachment with the electric vehicle port when the housing is mated with the electric vehicle port.

Abstract: A system for regulating charging of an electric aircraft 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 current. The at least a control signal conductor is configured to conduct a control signal. The controller is configured to receive a voltage datum from the electric aircraft, and regulate a charging voltage, as a function of the voltage datum, to the electric aircraft. Regulation of the charging voltage includes charging at least a battery of the electric aircraft in a plurality of phases including a first charging phase at a constant current and a second charging phase at a constant voltage.

Abstract: A monitoring system and method for charging multiple battery packs in an electric aircraft is illustrated. The system includes a plurality of submodules, a power bus element, and a computing device. The plurality of battery submodules is coupled to the electric aircraft and each battery submodules comprises a battery management component which comprises a sensor to detect a health metric. The power bus element is electrically connected to each battery submodule of the plurality of battery submodules. A computing device is connected at each battery submodule and is configured to receive the health metric form the sensor, determine a charging status of the battery submodule as a function of the health metric, and charge the battery submodules using the power bus element as a function of the charging status.

Abstract: In an aspect a connector for charging an electric aircraft, wherein the connector includes a housing includes to mate with an electric aircraft port of an electric aircraft. The connector also includes at least a current conductor configured to conduct a current. A current conductor may include a direct current conductor configured to conduct a direct current and an alternating current conductor configured to conduct an alternating current. A current conductor also includes at least a control signal conductor configured to conduct a control signal wherein each of the at least a conductor and the at least a control signal conductor are configured to make a connection with a mating component on the electric aircraft port when the housing is mated with the electric aircraft port. A connector further includes a proximity sensor and a controller. The controller may be configured to be communicatively connected to the proximity sensor.

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 for initiating a command of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to receive a topographical datum, receive a sensor datum from a sensor, identify an air position as a function of the sensor datum and the topographical datum, determine a command, including an actuator command, as a function of the identified air position and the determining of the command includes identifying at least one flight component of the eVTOL aircraft to be adjusted to perform the determined command, and initiate the command to adjust the identified flight component.

Abstract: A system and method for flight control of an aircraft, the flight control system including a plurality of flight components coupled to an aircraft, wherein the plurality of flight components includes a plurality of redundant control surfaces, a plurality of redundant low voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low voltage bus of the plurality of redundant low voltage busses does not impact the operability of the aircraft.