Abstract: An electric vehicle charger for an electric vehicle is provided. The electric vehicle charger includes a charging cable and a charging connector mechanically connected to the charging cable. The charging connector includes a rotation mechanism that may control a “pay in” and a “pay out” function of the electric vehicle charger, a cable reel configured to stow the charging cable, and a first idler drum associated with the cable reel. The first idler drum may produce a resultant force during the “pay out” function, thereby pushing the charging cable away from the cable reel. The rotation mechanism may include a rotary actuator mechanically connected to the cable reel. The rotary actuator may rotate the cable reel and produce the resultant force during the “pay out” function.

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: 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: 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: In an aspect of the present disclosure is a system for simulating an electrical vertical takeoff and landing (eVTOL) aircraft, including a fuselage comprising one or more pilot inputs, each of the pilot inputs configured to detect pilot datum; a concave screen facing the fuselage; a plurality of projectors directed at the concave screen; a computing device communicatively connected to the plurality of projectors, the computing device configured to: receive the pilot datum detected by the pilot inputs; generate a simulated eVTOL flight maneuver as a function of the pilot datum; and command the plurality of projectors to display one or more images based on the simulated flight maneuver.

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 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 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 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: A portable cockpit seat apparatus, the apparatus including a portable cockpit seat, wherein the portable cockpit seat includes a hinge and has a stowed position, wherein the portable cockpit seat is folded about the hinge. The apparatus further including a headset including a display, and at least a flight control communicatively connected to the headset. The headset configured to and display a cockpit view of an aircraft. The flight control of the at least a flight control is connected to the portable cockpit seat and the at least a flight control, in response to actuation by a user, is configured to send a thrust signal, wherein the thrust signal causes the aircraft to alter its thrust and send a lift signal, wherein the lift signal causes the aircraft to alter its lift.

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: In an aspect, a cockpit assembly is presented. A cockpit assembly includes at least a door. A cockpit assembly includes an inceptor stick. An inceptor stick includes a sheath movably connected thereon. An inceptor stick includes an actuator communicatively connected to a sheath. An actuator is configured to move a sheath between at least a door of a cockpit and an inceptor stick.

Abstract: An electric vehicle charger for an electric vehicle is provided. The electric vehicle charger includes a charging cable and a charging connector mechanically connected to the charging cable. The charging connector includes a rotation mechanism that may control a “pay in” and a “pay out” function of the electric vehicle charger, a cable reel configured to stow the charging cable, and a first idler drum associated with the cable reel. The first idler drum may produce a resultant force during the “pay out” function, thereby pushing the charging cable away from the cable reel. The rotation mechanism may include a rotary actuator mechanically connected to the cable reel. The rotary actuator may rotate the cable reel and produce the resultant force during the “pay out” function.

Abstract: In an aspect, a cockpit assembly is presented. A cockpit assembly includes at least a door. A cockpit assembly includes an inceptor stick. An inceptor stick includes a sheath movably connected thereon. An inceptor stick includes an actuator communicatively connected to a sheath. An actuator is configured to move a sheath between at least a door of a cockpit and an inceptor stick.

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: System and method for solution proposal workflow according to certain embodiments. For example, a method includes: generating an alert, the alert associated with one or more objects; identifying one or more possible solutions associated with the alert, the one or more possible solutions including one or more actions applicable to the one or more objects; applying a filter to the one or more possible solutions to select one or more solutions from the one or more possible solutions; and presenting the one or more selected solutions.

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.