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: 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: In an aspect, a propulsor gauge is provided that provides guidance during a transition of a mode of operation of an electronic 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: 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 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.

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, 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: A charging apparatus and method for charging an electric vehicle are disclosed. The apparatus includes a housing, a lid, a plurality of cables, and a power switch. The apparatus may further include one or more wheels, lights, and speakers, which are operated in accordance with the functionality of the apparatus. The apparatus can be connected to a 240 V AC wall outlet and output 600 V DC for high-power charging of an electric vehicle such as an aircraft.

Abstract: A charging apparatus and method for charging an electric vehicle are disclosed. The apparatus includes a housing, a lid, a plurality of cables, and a power switch. The apparatus may further include one or more wheels, lights, and speakers, which are operated in accordance with the functionality of the apparatus. The apparatus can be connected to a 240 V AC wall outlet and output 600 V DC for high-power charging of an electric vehicle such as an aircraft.

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.

Abstract: A ground service system for an electric aircraft is disclosed. The system includes a charging module including a charging cable electrically connected to an energy source and configured to charge a battery of the electric aircraft. The system also includes a cooling module including a cooling channel configured to fluidly couple the electric aircraft to a coolant source. The cooling module is configured to transmit a coolant from the coolant source and through the cooling channel to the electric aircraft to regulate a temperature of the battery of the electric aircraft. A controller of the cooling module is in communication with a battery management controller of the electric aircraft through a controller of the charging module.

Abstract: Embodiments of the disclosure provide an electric vehicle charger including a charger base housing an energy source, a charging cable coupled to the energy source, a charging connector for coupling the charging cable to an electric vehicle, and a cable storage device disposed within the charger base. The cable storage device includes: a reel rotatably disposed in the charger base. The charging cable is at least partially wrapped around the reel. A retraction mechanism is configured to rotate the reel to extend or retract the cable when activated. The retraction mechanism includes an electric motor operably coupled to the reel. A reel actuator is disposed on the charging connector and configured to activate the retraction mechanism. The reel actuator includes first and second user control elements for causing the electric motor to rotate in an extend or retract direction.

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: 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: A system and method for a recharging station including a landing pad, a rechargeable component coupled to the landing pad, a power delivery unit configured to deliver power from a power supply unit or power storage unit to the recharging component, and a support component coupled to the bottom of the landing pad.

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: 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: An electric vehicle charger, comprising: a transmitter coil electrically connected to an energy source and configured to inductively couple to a receiver coil on the electric vehicle; a proximity sensor configured to generate alignment data regarding the receiver coil on the electric vehicle and the transmitter coil; and a computing device that is communicatively connected to the proximity sensor, wherein the computing device is configured to: identify the electric vehicle using an authenticated identification datum from the electric vehicle; align the transmitter coil with the receiver coil as a function of the alignment data; and initiate charging of the electric vehicle as a function of the authenticated identification datum.

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.