Abstract: A system for controlling a flight boundary of an aircraft. The system includes a flight controller communicatively connected to the aircraft. The flight controller is configured to receive a plurality of flight data linked with the aircraft, determine a flight boundary for the aircraft as a function of the plurality of flight data, set an aircraft movement limit as a function of the flight boundary, receive a pilot instruction, and generate a control signal for the aircraft as a function of the aircraft movement limit and the pilot instruction. The control signal is limits the aircraft to remain within the flight boundary. A method for controlling a flight boundary of an aircraft is also provided.

Abstract: A method for the manufacturing of battery packs includes vertically stacking a plurality of battery cells to create a stack of battery cells, applying a compressive force on the stack of battery cells using a plurality of pneumatic cylinders, inserting a first portion of the compressed stack of battery cells into a container prior to releasing any of the plurality of pneumatic cylinders, engaging each of the battery cells of the plurality of battery cells with an end cap of the container, wherein the end cap is configured to maintain a predetermined arrangement of the plurality of battery cells, and releasing the first portion of the stack of battery cells from a first portion of the plurality of pneumatic cylinders while a second portion of the stack of battery cells remains compressed a second portion of the plurality of pneumatic cylinders.

Abstract: A system for automated flight correction in an electric aircraft includes an input control configured to generate a control datum, at least a sensor connected to the electric aircraft, wherein the at least a sensor is configured to detect a status datum, and a flight controller communicatively connected to the input control and the at least a sensor, wherein the flight controller is configured to determine a command datum as a function of the control datum and the status datum, wherein determining the command datum comprises comparing the control datum to a limitation set based on the status datum, and calculating a modified control datum based on a flight plan of the electric aircraft through a remote device.

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: A system and method for an electric aircraft with a plurality of battery packs in a battery bay are illustrated. The system comprises a least a propulsion component, a fuselage with an elongated base wherein the elongated base includes a battery bay, and a plurality of battery packs inserted in the battery bay, wherein the plurality of battery packs is configured to provide electrical power to the at least a propulsion component.

Abstract: A system for managing residual energy for an electric aircraft, wherein the system includes a battery pack incorporated in the electric aircraft, wherein the battery pack includes a plurality of battery modules and at least a pack monitor unit configured to generate a battery pack datum. The system further includes a charging component connected to the battery pack and a sensor connected to the charging component and configured to detect at least an electrical parameter of the charging component and the electric aircraft and generate a residual datum as a function of the at least an electrical parameter and the battery pack datum. The system further includes a computing device configured to receive the residual datum from the sensor, identify a residual element, generate an alert datum as a function of the residual element, and execute a security measure as a function of the alert datum.

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: A high energy density battery module may comprise a plurality of battery units. The battery units may be electronically coupled to at least one other battery unit and may further comprise a plurality of electrochemical battery cells. The battery units may comprise a cell retainer to fix cells in a predetermined arrangement comprising a first and second column of battery cells. The battery units may comprise protective wrapping of thermally insulating material woven between at least a portion of the first and second column of battery cells. An electrical contact may be may be disposed in or on each of the plurality of battery units.

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 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 and method for charging multiple battery packs in an electric aircraft is illustrated. The system includes a plurality of submodules, a power bus element, and a computing device. The plurality of battery submodules is coupled to the electric aircraft and each battery submodules comprises a battery management component which comprises a sensor to detect a health metric. The power bus element is electrically connected to each battery submodule of the plurality of battery submodules. A computing device is connected at each battery submodule and is configured to receive the health metric form the sensor, determine a charging status of the battery submodule as a function of the health metric, and charge the battery submodules using the power bus element as a function of the charging status.

Abstract: A system for aircraft power management and distribution, including a sensor suite configured to measure battery pack data. The system includes a battery pack with a plurality of batteries and a battery monitoring component. This battery monitoring component is configured to measure battery pack data. The system also has electric power converters, each connected to a battery of the plurality of batteries. The system also includes a controller configured to control each electric power converter; receive an estimated charge from each battery; select and enable electric power converters based on the estimated charge; compare the total output of the enabled electric power converters against an optimal operating region; and adjust the number of the one or more enabled electric power converters accordingly.

Abstract: A system for reducing air resistance in an electric aircraft flight that comprises at least a flight component connected to the electric aircraft and at least a sensor connected to the at least a flight component, wherein the at least a sensor is configured to detect a status datum of the at least a flight component and transmit the status datum to a computing device communicatively connected to a electric aircraft, wherein the computing device is configured to receive the status datum from the at least a sensor, generate an optimum position of the at least a flight component as a function of the status datum and initiate the optimum position of the at least a flight component.

Abstract: An electric aircraft charging connector, including a direct current pin and/or an alternating current pin. The connector including a ground pin, the ground pin providing a grounded connection. The connector also including a resistance sensor, the resistance sensor electrically connected to the direct current pin and/or the alternating current pin, and the ground pin, the resistance sensor configured to measure a resistance datum, the resistance datum including: a first resistance, the first resistance comprising a measurement of resistance between the direct current pin and the ground pin; and a second resistance, the second resistance comprising a measurement of resistance between the alternating current pin and the ground pin. The connector also including a controller, the controller configured to: receive the resistance datum from the resistance sensor; and compare the resistance datum to a threshold resistance datum.

Abstract: A system and method for managing residual energy in a charging component is disclosed herein. Managing residual energy includes detecting an electrical parameter of the charging component and the electrically connected battery pack and generating a residual datum. The residual datum is transmitted to a computing device. The computing device identifies a residual element, generates an alert datum, and executes a security measure.

Abstract: A system for a shutdown of an electric aircraft port in response to a fault detection is presented. The system includes a sensor communicatively connected to a charging component, wherein the sensor is configured to detect at least a measured charger datum and generate a sensor datum as a function of the at least a measured charger datum. The system further includes a computing device, wherein the computing device is configured to identify a fault element as a function of the sensor datum, determine a disruption element as a function of the identification of the fault element. and initiate a shutdown protocol of the port as a function of the disruption element.

Abstract: In an aspect, an electric aircraft port having a ventilation system is provided. Electric aircraft port 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: A system for a shutdown of an electric charger of an electric vehicle in response to a fault detection is presented. The system includes a sensor communicatively connected to a charging component, wherein the sensor is configured to detect at least a measured charger datum and generate a sensor datum as a function of the at least a measured charger datum. The system further includes a computing device, wherein the computing device is configured to identify a fault element as a function of the sensor datum, determine a disruption element as a function of the identification of the fault element. and initiate a shutdown protocol of the charging component as a function of the disruption element.

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 regulating charging of an electric aircraft includes a charging connector and a controller communicatively connected to the charging connector. The charging connector includes a housing, at least a conductor, and at least a control signal conductor. The housing is configured to mate with an electric aircraft port of an electric aircraft. The at least a conductor is configured to conduct a current. The at least a control signal conductor is configured to conduct a control signal. The controller is configured to receive a voltage datum from the electric aircraft, and regulate a charging voltage, as a function of the voltage datum, to the electric aircraft. Regulation of the charging voltage includes charging at least a battery of the electric aircraft in a plurality of phases including a first charging phase at a constant current and a second charging phase at a constant voltage.