Abstract: In an aspect a system for electric charger communication is presented. A system includes a first networking component and sensor of a first electric charger. The system includes at least a processor communicatively connected to a first networking component and the sensor. The system includes memory communicatively connected to at least a processor, wherein the memory contains instructions configuring at least a processor to receive the at least a charger metric from the sensor and transmit the at least a charger metric to the network using the first communicative connection, wherein the at least a charger metric comprises a charger status.

Abstract: A system for data communication for an electric aircraft is disclosed. The system may include a charging connector configured to mate with at least an electric aircraft port of the electric aircraft. The charging connector may be further configured to charge at least a battery pack of the electric aircraft, wherein the charging connector may include a housing configured to house at least a component of the charging connector and a pin configured to connect conductors. The system may include a computing device communicatively connected to the charging connector, wherein the computing device is configured to establish a data connection with the electric aircraft. The computing device is further configured to receive data over the data connection from the electric aircraft at a data transfer rate.

Abstract: In an aspect the current disclosure is directed to an electric vehicle charger for an electric vehicle. The electric vehicle charger is comprised of an energy source, a transmitter coil electrically connected to the energy source and configured to wirelessly conduct a current in a receiver coil using induction, at least a proximity sensor configured to generate alignment data relating to an electric vehicle, and a computing device that is communicatively connected to the at least a proximity sensor. The computing device may be configured to identify the electric vehicle. Identification may include receiving and authenticating at least an identification datum, and identifying the electric vehicle using that; The computing device is configured to align the transmitter coil with the receiver coil using the alignment data. Additionally, the computing device may be configured to authorize the electric vehicle to be begin charging as a function of the authentication.

Abstract: A system of pay-in and pay-out function of a cooling system for an electric vehicle and a method of use is presented in this disclosure. The system may include a cooling cable, a cooling connector, wherein the cooling connector may include an actuator, a cable reel, and an idler drum. The cable reel may include a helical pattern where the cooling cable resides during the stowed configuration. The idler drum may be parallel to the cable reel.

Abstract: In an aspect, a propulsor gauge is provide that provides guidance during a transition of a mode of operation of an electric aircraft. Propulsor gauge may include a processor configured to identify a current thrust envelope parameter of one or more propulsors of electric aircraft. Processor may also determine a recommended range as a function of the propulsor parameter, where the recommended range includes a lower threshold and an upper threshold. The recommended range and thrust envelope parameter may then be shown on a display of propulsor gauge, where a measurement of current thrust envelope parameter relative to recommended range may be represented by an indicator.

Abstract: The present invention is systems and methods for preflight temperature management of an energy source of an electric aircraft. The system may include a sensor attached to an energy source of an electric aircraft, where the sensor is configured to detect a temperature of the energy source and generate a corresponding temperature datum. A computing device communicatively connected to the sensor may receive the temperature datum and determine the readiness of the electric aircraft for flight based on the temperature of the energy source. If the electric aircraft is not considered ready by the computing device, then an energy source modification may be initiated that changes the temperature of the energy source.

Abstract: Aspects relate to a connector and methods of use for charging an electric aircraft. An exemplary connector includes a housing configured to mate with a port of an electric aircraft, where the housing includes a fastener for removable attachment with the electric aircraft port, at least a high-voltage conductor configured to conduct a high-voltage electrical power, at least a low-voltage conductor, configured to conduct a low-voltage electrical power, 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 cooling channel 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 aircraft port when the housing is mated with the port.

Abstract: A system for an electric vehicle charger with a reel button for an electric vehicle is illustrated. The system comprises a charging cable, a charger base connected to the charging cable, a cable storage device, the cable storage device including a retraction mechanism configured to pay out and retract the cable when activated and at least a reel button configured to activate the retraction mechanism.

Abstract: An apparatus and a method for an indicating system for ground support equipment for an electric aircraft is disclosed. The apparatus may include ground support equipment, wherein the ground support equipment may include at least a ground support module, wherein the at least a ground support module may be configured to support an operation of an electric aircraft, one or more housings, wherein the one or more housings may be configured to house the at least a ground support module, a cable module, wherein the cable module may be configured to connect the at least a ground support module and the electric aircraft, an indicator configured to indicate informatic communication of the at least ground support module and the cable module and a controller communicatively connected to the at least a ground support module and the cable module and configured to control the indicator.

Abstract: An apparatus for guiding a transition between flight modes of an electric aircraft is illustrated. The apparatus comprises at least a sensor configured to detect a movement datum of the electric aircraft and a flight controller communicatively connected to the at least sensor, wherein the flight controller is configured to receive the movement datum from the at least a sensor, determine a current flight mode of the electric aircraft as a function of the movement datum, generate a guidance datum as a function of a change in flight mode and the movement datum, communicate the movement datum and the guidance datum to a pilot indicator in communication with the flight controller, and display the movement datum and the guidance datum using the pilot indicator.

Abstract: An apparatus for automated ground control of an electric vertical takeoff and landing aircraft includes a flight controller and a remote device. Remote device may transmit a location datum to a flight controller. Location datum may store a location of a charger, terminal, airport, or the like. Flight controller may authorize the location datum and direct aircraft using the information from the location datum.

Abstract: In an aspect an apparatus for determining a most limiting parameter of an electric aircraft is presented. An apparatus includes at least a processor and a memory communicatively connected to the at least a processor. A memory contains instructions configuring at least a processor to receive aircraft data from a sensing device. A sensing device is configured to measure a parameter of an electric aircraft and generate aircraft data. At least a processor is configured to determine a most limiting parameter of an electric aircraft as a function of aircraft data. At least a processor is configured to communicate a most limiting parameter to a pilot indicator in communication with the at least a processor and memory communicatively connected to the at least a processor. A pilot indicator is configured to display a most limiting parameter to a user.

Abstract: A ground service system for an electric aircraft is disclosed. The system includes a charging module configured to charge a battery of an electric aircraft. The charging module includes a charging cable electrically connected to an energy source. The system includes a cooling module configured to regulate a temperature of the battery. The cooling module includes a cooling cable configured to carry a coolant. The system also includes a cabin soak module configured to provide a cabin soak coolant to a cabin of the electric aircraft. The cabin soak module includes a cabin soak cable configured to carry a fluid.

Abstract: In an aspect the current disclosure may describe a electric charging station for an electric vehicle. The electric charging station may include a charging cable, wherein the charging cable is configured to carry electricity and an energy source, wherein the energy source is electrically connected to the charging cable. The charging station may further include a temperature sensor, wherein the temperature sensor is configured to generate temperature datum and a computing device. A computing device may be communicatively connected to the plurality of temperature regulating elements and the temperature sensor. The computing device may further be configured to receive the battery datum and regulate battery temperature and cabin temperature using the plurality of temperature regulating elements as a function of the temperature datum.

Abstract: In an aspect an apparatus for determining a most limiting parameter of an electric aircraft is presented. An apparatus includes at least a processor and a memory communicatively connected to the at least a processor. A memory contains instructions configuring at least a processor to receive aircraft data from a sensing device. A sensing device is configured to measure a parameter of an electric aircraft and generate aircraft data. At least a processor is configured to determine a most limiting parameter of an electric aircraft as a function of aircraft data. At least a processor is configured to communicate a most limiting parameter to a pilot indicator in communication with the at least a processor and memory communicatively connected to the at least a processor. A pilot indicator is configured to display a most limiting parameter to a user.

Abstract: In an aspect an apparatus for determining a most limiting parameter of an electric aircraft is presented. An apparatus includes at least a processor and a memory communicatively connected to the at least a processor. A memory contains instructions configuring at least a processor to receive aircraft data from a sensing device. A sensing device is configured to measure a parameter of an electric aircraft and generate aircraft data. At least a processor is configured to determine a most limiting parameter of an electric aircraft as a function of aircraft data. At least a processor is configured to communicate a most limiting parameter to a pilot indicator in communication with the at least a processor and memory communicatively connected to the at least a processor. A pilot indicator is configured to display a most limiting parameter to a user.

Abstract: In an aspect the current disclosure is directed to an electric vehicle charger for an electric vehicle. The electric vehicle charger is comprised of an energy source, a transmitter coil electrically connected to the energy source and configured to wirelessly conduct a current in a receiver coil using induction, at least a proximity sensor configured to generate alignment data relating to an electric vehicle, and a computing device that is communicatively connected to the at least a proximity sensor. The computing device may be configured to identify the electric vehicle. Identification may include receiving and authenticating at least an identification datum, and identifying the electric vehicle using that; The computing device is configured to align the transmitter coil with the receiver coil using the alignment data. Additionally, the computing device may be configured to authorize the electric vehicle to be begin charging as a function of the authentication.

Abstract: Electric aircraft charging system including charging cable configured to carry electricity and energy source, wherein the energy source is electrically connected to the charging cable. The system also including a cable reel module, the cable reel module including a reel, wherein the reel is rotatably mounted to the cable reel module, wherein the reel is configured to rotate in a forward direction and a reverse direction, and the charging cable, in a stowed configuration, is wound around the reel. The cable reel module further including a rotation mechanism configured to rotate the reel in reverse, and a cable reel module door having a closed position and an open position, wherein the closed position prevents access to the reel and the open position allows access to the reel. The system additionally including a controller communicatively connected to the rotation mechanism and configured to send a retraction signal to the rotation mechanism.

Abstract: An apparatus for guiding a transition between flight modes of an electric aircraft is illustrated. The apparatus comprises at least a sensor configured to detect a movement datum of the electric aircraft and a flight controller communicatively connected to the at least sensor, wherein the flight controller is configured to receive the movement datum from the at least a sensor, determine a current flight mode of the electric aircraft as a function of a pilot input and the movement datum, generate a guidance datum as a function of a change in flight mode and the movement datum, and communicate the guidance datum to a pilot indicator in communication with the at least a sensor and flight controller communicatively connected to the at least a sensor.

Abstract: A system for monitoring impact on an electric aircraft is presented. The system includes a sensor communicatively connected to a flight component, wherein the sensor is configured to detect a measured force datum and generate an impact datum as a function of the measured force datum. The system further includes a computing device configured to simulate a landing performance model output as a function of the impact datum, generate a landing performance datum as a function of a comparison between the landing performance model output, determine an alert datum as a function of the landing performance datum, and display the landing performance datum on a user device.