Abstract: An apparatus for a locking thermal conditioning hose for an electric aircraft, the apparatus comprising a thermal conditioning hose comprising a thermal medium flow path configured to contain a flow of a thermal medium, a thermal medium return path, the thermal medium return path configured to contain a flow of the thermal medium from an electric aircraft, and a mating component, wherein the mating component is configured to make a connection with an electric aircraft port, and a thermal latch, wherein the thermal latch is configured to couple the thermal conditioning hose to the electric aircraft.

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: 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 for landing spot analysis including an electric aircraft and a sensor connected to the electric aircraft. The sensor is configured to detect a landing datum relating to a possible landing spot, wherein the landing datum comprises information regarding the physical properties of the possible landing spot. The system also including a controller onboard the electric aircraft and communicatively connected to the sensor. The controller is configured to receive a command identifying at least the possible landing spot, receive the landing datum from the sensor, generate a landing determination as a function of the landing datum, wherein the landing determination relates to the suitability of the possible landing spot and generating the landing determination includes transmitting a landing request to air traffic control, and transmit the landing determination to a pilot.

Abstract: Aspects relate to a cooling system for a power supply of an electric aircraft. A cooling system may regulate a temperature of one or more components of a power supply, such as an energy source, a charging port, conductors, and the like. A cooling system may include a channel that a coolant may flow therethrough, where the coolant absorbs heat from the power supply to reduce the temperature of the power supply.

Abstract: A system for charger management for electrical vertical takeoff and landing aircrafts includes a sensor connected to the first charger. The sensor is configured to detect a battery metric and transmit the metric to a computing device. The computing device is connected to a mesh network. The mesh network contains many aircrafts connected to chargers. The charger management system manages the charging of the aircraft.

Abstract: Aspects relate to a system for discharging a power source of an electric aircraft. System may be configured to transfer power from the electric aircraft via a charging connection. In one or more embodiments, a charging station in electric communication with the power source may discharge the power source. For example, a controller communicatively connected to the electric aircraft may be configured to receive a supply request from a user and subsequently, generate a control signal that initiates a transfer of electrical power from the power supply to discharge the power source so that power data associated with the discharge may be collected and transmitted to the controller or a remote device of the user.

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 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 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 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: A system and method for the management of recharging multiple electric vertical takeoff and landing aircrafts is presented. The system comprises a common recharging component and a computing device. The computing device is communicatively connected to a plurality of electric vertical takeoff and landing aircrafts, wherein the computing device is configured to receive flight inputs of each electric vehicle of the plurality of electric vertical takeoff and landing aircrafts from a plurality of sensors, and determine a recharging method as a function of the flight inputs and the flight inputs comparison.

Abstract: An apparatus for generating an electric aircraft flight plan, where the apparatus includes a sensor and controller. The electric aircraft includes a sensor that is configured to detect a position of an electric aircraft, generate a position datum, and transmit the position to a flight controller. The electric aircraft also includes a database of recommended flights. The recommended flight plan is displayed on a display in the electric aircraft.

Abstract: Aspects relate to methods and systems for optimizing battery recharge management for use with an electric vertical take-off and landing aircraft. An exemplary system includes an electric vertical take-off and landing (eVTOL) aircraft comprising at least battery mechanically coupled to the eVTOL aircraft cand configured to power at least an aircraft component of the eVTOL aircraft, wherein the at least a battery comprises a plurality of battery cells, and at least a sensor, configured to measure battery data associated with the at least a battery, and a server remote from the eVTOL and in communication with the at least a sensor, wherein the server is configured to receive the battery data from the at least a sensor, receive mission data associated with a planned flight mission of the eVTOL aircraft, and generate a recharge time as a function of the battery data and the mission data.

Abstract: Aspects relate to a system for flight plan generation of an electric vertical takeoff and landing (eVTOL) aircraft. An exemplary system for flight plan generation includes a flight controller mounted on an eVTOL aircraft. The flight controller may be configured to receive a plurality of flight plan data and generate a flight plan for the aircraft as a function of the plurality of flight plan data.

Abstract: An apparatus for generating an electric aircraft flight plan, where the apparatus includes a sensor and controller. The electric aircraft includes a sensor that is configured to detect a position of an electric aircraft, generate a position datum, and transmit the position to a flight controller. The electric aircraft also includes a database of recommended flights. The recommended flight plan is displayed on a display in the electric aircraft.

Abstract: A system and method for its use for determining a suitable battery pack combination configured for use in an electric aircraft, the system including at least a processor connected to a sensor and a memory containing instructions configuring the at least a processor to receive battery pack status data for each battery pack of a plurality of battery packs, generate a battery pack diagnostic datum for each battery pack of the plurality of battery packs as a function of the battery pack status data of each battery pack of the plurality of battery packs, and determine a suitability of the plurality of battery packs as a function of each battery pack diagnostic datum for each battery pack of the plurality of battery packs.

Abstract: Aspects relate to a system for flight plan generation of an electric vertical takeoff and landing (eVTOL) aircraft. An exemplary system for flight plan generation includes a flight controller mounted on an eVTOL aircraft. The flight controller may be configured to receive a plurality of flight plan data and generate a flight plan for the aircraft as a function of the plurality of flight plan data.