Abstract: A system for recharging an electric vehicle including a recharging component, wherein the recharging component is configured to supply power to an energy source of an electric vehicle, a sensor, wherein the sensor is configured to detect a plurality of data regarding the electric vehicle and generate an environment datum as a function of the plurality of data, a ventilation system, wherein the ventilation system is communicatively connected to the recharging component and a control pilot, wherein the control pilot is in electronic communication with the sensor, wherein the control pilot is configured to receive the environment datum from the sensor, generate a ventilation requirement datum as a function of the environment datum and command the ventilation system to perform a ventilation process as a function of the ventilation requirement datum.

Abstract: A system for a rotor with directional magnetic field configured for use in electric aircraft motor that includes a magnet array having an outer cylindrical surface, an inner cylindrical surface, an upper edge, and a lower edge, which further includes a plurality of magnets, where the plurality of magnets is configured to create a directional magnet field and an electrically insulating epoxy, where the electrically insulating epoxy envelops at least a portion of the plurality of magnets.

Abstract: A system for charging multiple power sources including a plurality of batteries. The system also including a plurality of diodes, each diode of the plurality of diodes electrically connected in series with at least a battery of the plurality of batteries, wherein each diode of the plurality of diodes restricts current flow into the plurality of batteries and the plurality of diodes permits current flow from the plurality of batteries. The system includes a bus element connecting the batteries in parallel, having a cross tie element having an engaged state and disengaged state. The bus element disconnects a first battery from a second battery of the plurality of when the cross-tie element is in the disengaged state, and connects the first battery to the second battery when the cross tie element is in the engaged state. The system includes a load electrically connected to the plurality of diodes.

Abstract: A monitoring system for charging multiple battery packs in an electric aircraft, the system comprising a plurality of battery packs included in an electric aircraft, wherein each battery pack comprises a battery management component comprising at least a sensor configured to detect a health metric, a power bus element, wherein the power bus element is electrically connected to each battery pack of the plurality of battery packs, and a charger electrically connected to the power bus element comprising a computing device communicatively connected to each battery pack, wherein the computing device is configured to receive the plurality of health metrics from the plurality of at least a sensor, determine a charging status of each of the plurality of battery packs as a function of the plurality of health metrics, wherein a charge capacity value of each of the plurality of health metrics is compared to a charge threshold value, and wherein the charger is configured to charge each of the plurality of battery packs u

Abstract: An apparatus for a ground-based battery management for an electric aircraft is presented. The apparatus includes a battery pack mechanically coupled to the electric aircraft, the battery pack includes at least a battery module that includes at least a battery unit that includes battery cells and a thermal conduit configured to transfer heat between the battery cells and the thermal conduit and a thermal circuit mechanically coupled to the thermal conduit configured to facilitate the heat transfer using thermal media. The apparatus includes a media channel communicatively connected to a computing device and comprising at least a sensor, wherein the media channel is configured to evacuate the thermal media out of the battery pack using the thermal circuit and the computing device that includes a battery management system is configured to receive a condition parameter as a function of the at least a sensor of the media channel.

Abstract: A fuel pod for a hybrid electric aircraft. The fuel pod includes a housing, a fuel tank, a generator and a connection mechanism. The fuel tank is contained within the housing and is configured to hold a fuel therein. The generator is contained within the housing and is connected to the fuel tank. The generator is configured to power at least one of a plurality of flight components of a hybrid electric aircraft. The connection mechanism is at the housing and is configured to removably attach the fuel pod to the hybrid electric aircraft. The connection mechanism includes an electrical interface configured to electrically link to at least one of the plurality of flight components of the hybrid electric aircraft, and a communication interface configured to communicatively link to a flight controller communicatively connected to the hybrid electric aircraft.

Abstract: A system for stowable propulsion in an electric aircraft that includes at least a propulsor mounted on at least a structural feature that includes at least a rotor and at least a motor mechanically coupled to the at least a rotor, where the motor is configured to cause the rotor to rotate as a function of an activation datum, at least a sensor communicatively coupled to the at least a propulsor configured to detect a position datum as a function of the configuration, generate a clearance datum as a function of the position datum, transmit the clearance datum to a flight controller, and a flight controller communicatively coupled to the at least a propulsor and the at least a sensor configured to receive the clearance datum from the at least a sensor and generate the activation datum as a function of the clearance datum.

Abstract: A system and method for redundant electric power for an electric aircraft is provided. The system includes a plurality of battery packs which includes at least a first pack monitor unit and at least a second pack monitor unit configured to detect a first battery pack datum and a second battery pack datum, and transmit the pair of battery pack datum to a controller. Each battery pack. The system further includes a contactor coupled to the electric aircraft, a plurality of loads communicatively coupled to each battery pack of the plurality of battery packs, and a controller, wherein the controller is designed and configured to receive the first battery pack and the second battery pack datum, compare the first battery pack datum to the second battery pack datum as a function of a differential threshold, and generate an alert datum as a function of the comparison.

Abstract: The present invention is a system and methods for an immediate shutdown of an electric vehicle charger. The system may include a sensor, which is communicatively connected to a charging connection, and a control circuit, which is communicatively connected to the sensor. If a disruption element is determined by the control circuit as a function of a charging datum of the sensor, then control circuit is configured to conduct an immediate shutdown of charger by disabling a communication of a charging connection to prevent harm to an electric vehicle, a charger, and/or a user.

Abstract: In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.

Abstract: A power source assembly for an electric eVTOL aircraft comprising a battery pack. The battery pack further comprising an end panel, a plurality of high energy density battery modules, wherein each module comprises a plurality of battery units, further comprising a plurality of battery cells electronically coupled together, a cell retainer disposed in a predetermined arrangement comprising two columns, a protective wrapping of thermally insulating material woven between columns of battery units, and a terminal electronically disposed on the end panel electronically connected to each of the plurality of high energy density battery modules.

Abstract: In an aspect, a system comprising a computing device. The computing device is configured to determine a drag minimization axis of a rotor connected to an aircraft. The rotor includes a first end and a second end. The rotor is configured to rotate about an axis. The computing device is further configured to determine a halting point of the rotor, wherein the halting point includes a drag minimization axis of the rotor. The computing device is configured to send a halting command to at least a magnetic element to halt the rotor, wherein the halting process is configured to stop a movement of the rotor and position the rotor in the halting point. The position of the rotor in the halting point includes the first end pointing in one direction of the drag minimization axis and the second end pointing in an opposite direction of the first end.

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: In an aspect the current disclosure is an apparatus for authorizing an electric aircraft to charge at a charging structure. The apparatus may include a housing configured to mate with an electric vehicle port of an electric vehicle, at least a current conductor configured to conduct a current, a proximity sensor, and a computing device. The at least a current conductor comprises a direct current conductor configured to conduct a direct current and an alternating current conductor configured to conduct an alternating current. The computing device is configured to be communicatively connected to the aircraft charging structure and the proximity sensor. The computing device may further be configured to receive an aircraft credential from an aircraft controller, authorize the charging structure to charge an energy source of the aircraft as a function of the aircraft credential, and upload the aircraft credential to a remote data storage device.

Abstract: A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.

Abstract: A distributed control system with supplemental attitude adjustment including an aircraft control having an engaged state and a disengaged state. The system also including a plurality of flight components and a plurality of aircraft components communicatively connected to the plurality of flight components, wherein each aircraft component is configured to receive an aircraft command and generate a response command directing the flight components as a function of supplemental attitude. The supplemental attitude based at least in part on the engagement datum and generating a supplemental attitude includes choosing a position supplemental attitude if the aircraft control is disengaged and choosing a velocity supplemental attitude if the aircraft control is engaged. In generating the response command, the aircraft attitude is combined with the supplemental attitude to obtain an aggregate attitude, and the aircraft component is configured to generate the response command based on the aggregate attitude.

Abstract: In an aspect, a system for recharging an electric vehicle. A system includes a recharging component. A recharging component includes a ventilation system. A system includes a sensor configured to detect a plurality of data from the recharging component. A sensor is configured to generate an environment datum as a function of the plurality of data. A system includes a control pilot. A control pilot is in electronic communication with a sensor. A control pilots is configured to receive an environment datum from a sensor. A control pilot is configured to generate a ventilation requirement datum from an environment datum. A control pilot is configured to command a recharging component to perform a ventilation process. A system includes a pilot display. A pilot display is coupled to an electric vehicle. A pilot display is configured to display a ventilation requirement datum to a pilot.

Abstract: The present disclosure is generally directed to a flight control system and method of flight control for an electric aircraft. The system includes a pilot input communicatively connected to an electric aircraft, wherein the pilot input is configured to receive an input datum, and plurality of flight components communicatively connected to the electric aircraft, wherein the plurality of flight components includes a plurality of control surfaces. The system also includes a flight controller, wherein the flight controller is configured to determine a phase of flight, determine a command datum to control a position of the plurality of control surfaces as a function of the input datum, and command, when the phase of flight is determined to be hover, the plurality of control surfaces using the command datum.

Abstract: A system and method for autonomous flight control with mode selection an electric aircraft is illustrated. The system comprises an altitude-related sensor and a computing device. The altitude-related sensor is coupled to the electric aircraft and is configured to detect an altitude value. The computing device is communicatively connected to the altitude-related sensor and is configured to receive the altitude value from the altitude-related sensor, to determine a flight mode as a function of the altitude value and an altitude threshold, to determine an aircraft adjustment as a function of a determine flight mode, and to generate an autonomous function configured to enact the determined flight mode and an aircraft adjustment automatically.

Abstract: A system for emergency shutdown of an electric charger in response to a disconnection is presented. The system includes a computing device, wherein the computing device is configured to receive a sensor datum from a sensor, determine a disruption element between a charging connector and an electric vehicle as a function of the sensor datum, and initiate a disconnection protocol as a function of the disruption element.