Abstract: A battery assembly for use in an electric aircraft, the battery assembly including a plurality of battery cells, four opposite and opposing sides, where at least two sides are angled inward as to secure the plurality of battery cells inside the battery assembly, and at least a sensor, where the at least a sensor is configured to detect a thermal runaway.

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 initiating a command of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to receive a topographical datum, identify an air position as a function of a sensor and the topographical datum, wherein identifying further comprises obtaining a sensor datum as a function of the sensor, and identifying the air position as a function of the sensor datum and the topographical datum using a similarity function, determine a command as a function of the air position, and initiate the command.

Abstract: A system for restricting power to a load to prevent engaging a circuit protection device for an electric aircraft includes an energy source. The energy source is communicatively coupled to a load, wherein the load includes a portion of a propulsion system. The system includes sensors configured to sense an electrical parameter. The system includes an aircraft controller communicatively connected to the energy source, wherein the aircraft controller is configured to receive an electrical parameter, compare the electrical parameter to a current allocation threshold, detect that the electrical parameter has reached a current allocation threshold, calculate a power reduction to the load, generate a current allocation threshold notification as a function of the detection, wherein the current allocation threshold notification indicates that the electrical parameter has reached the current allocation threshold.

Abstract: A system and method for management of propulsors for an electric aircraft, where the electric aircraft is configured to transition between a hover state and a fixed-wing flight state. The electric aircraft may include at least one set of a plurality of propulsors coupled to the electric aircraft. A flight controller may be coupled to the electric aircraft and configured to detect a state transition of the electric aircraft from the hover state to the fixed-wing flight state and send a parking command to the at least one set of a plurality of propulsors.

Abstract: An electric aircraft charging connector, including a set of pins, a sensor, a controller, and a locking mechanism. The set of pins may include an AC pin, the AC pin configured to supply AC power to a charging port and/or a DC pin, the DC pin configured to supply DC power to the charging port. The sensor can detect power flow from the pins to the charging port. The controller is communicatively connected to the sensor and configured to receive a signal from the sensor and send a locking signal to a locking mechanism. The locking mechanism is communicatively connected to the controller, having an engaged state wherein the charging connector is mechanically coupled to the charging port and a disengaged state wherein the charging connector is mechanically uncoupled form the charging port, the locking mechanism configured to receive a locking signal from the controller and enter the engaged state.

Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a fuselage, a plurality of laterally extending elements, a plurality of propulsors, a flight controller, and a pilot override switch. The plurality of laterally extending elements are attached to the fuselage. The plurality of propulsors is attached to the plurality of laterally extending elements. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a flight transition point, initiate rotation about an axis of the fuselage a as function of the flight transition point, and terminate rotation once the desired flight angle is reached.

Abstract: A system, method and computer program product for communicating data of a vehicle. The system includes a data recording device and a data transmitting device coupled to the vehicle. The data recording device is configured to receive at least a vehicle datum during operation of the vehicle, determine a subset of the at least a vehicle datum to be stored, wherein the subset of data is stored during operation of the vehicle, and store the subset of the at least a vehicle datum as a stored vehicle data, wherein the stored vehicle data comprises a diagnostic datum of a vehicle component. The data transmitting device is configured to initiate communication with an independent data communication device as a function of a connection to a network and transmit the stored vehicle data to the independent data communication device as a function of the connection to the network.

Abstract: A system for dynamic excitation of an energy storage element configured for use in an electric aircraft includes a plurality of propulsors mechanically connected to the electric aircraft. The system includes a plurality of energy storage elements electrically connected to the plurality of propulsors. The system includes a bus element, wherein the bus element is electrically connected to the plurality of energy storage elements and a cross tie element connected to the bus element configured to disconnect a first energy storage element from a second energy storage element. The system includes a modulator unit electrically connected to the bus element configured to modulate a first electrical command to the first energy storage element and a second electrical command to the second energy storage element. The system includes at least a sensor configured to detect an energy datum corresponding to the first energy storage element as a function of the modulation.

Abstract: Aspects relate to a charger for an electric aircraft with failure monitoring and method for its use. An exemplary charger for an electric aircraft with failure monitoring includes a charging circuit. Included within the charging circuit is a connector configured to mate with an electric aircraft port of an electric aircraft and at least a current conductor configured to conduct a current. At least a conductor comprises a direct current conductor configured to conduct a direct current; and an alternating current conductor configured to conduct an alternating current. A charger may include a control circuit configured to command the charging circuit of an electric aircraft as a function of charging datum. A charger may also include a failure monitor circuit, the failure monitor circuit configured to: detect a failure and initiate a failure mitigation procedure as a function of failure detection.

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 mitigating charging failure for an electric aircraft including a charging connector, a sensor, a charger, and a controller. The charging connector comprising at least a charging pin and configured to mate with a corresponding charging port on an electric aircraft. The sensor communicatively connected to the charging connector and configured to detect a charging datum. The charger electrically connected to the charging connector and comprising a power source electrically connected to the charging connector. The controller communicatively connected to the sensor and configured to receive a charging datum from the sensor, detect a charging failure as a function of the charging datum, and initiate a mitigating response in response to detecting a charging failure.

Abstract: A system and method for the overcurrent protection in an electric vehicle is illustrated. The system comprises an AC pin, a DC pin, an electric vehicle charging connector, wherein the electric vehicle charging connector comprises a protection circuit, wherein the protection circuit is configured to control a transmission of power through the electric vehicle charging connector, a sensor, wherein the sensor is configured to detect an output current, and a controller communicatively connected to the sensor. The controller is configured to detect an overcurrent output as a function of the output current and trip the protection circuit as a function of the overcurrent output.

Abstract: A system for restricting power to a load to prevent engaging a circuit protection device for an electric aircraft includes an energy source. The energy source is communicatively coupled to a load, wherein the load includes a portion of a propulsion system. The system includes sensors configured to sense an electrical parameter. The system includes an aircraft controller communicatively connected to the energy source, wherein the aircraft controller is configured to receive an electrical parameter, compare the electrical parameter to a current allocation threshold, detect that the electrical parameter has reached a current allocation threshold, generate a current allocation threshold notification as a function of the detection, wherein the current allocation threshold notification indicates that the electrical parameter has reached the current allocation threshold.

Abstract: A system for communicating at least a pre-charging datum for an electric vehicle, the system including an electric aircraft, wherein the electric aircraft comprises, a sensor, wherein the sensor is configured to detect a connection with a charging connector, at least a battery pack, wherein the at least a battery pack including a plurality of battery cells, an aircraft recharging component, the aircraft recharging component including an aircraft side recharging component, wherein the aircraft side recharging component is configured to form a charge connection with the charging connector, a controller, wherein the controller is configured to generate a battery parameter set as a function of the connection with the charging connector, and transmit the battery parameter set to the charging connector.

Abstract: Aspects relate to an electric aircraft having a two-motor propulsion system and methods for use. An exemplary electric aircraft includes a flight component attached to the electric aircraft, where the flight component is configured to generate thrust, a first electric motor and a second electric motor, where each of the first electric motor and the second electric motor are mechanically connected to the flight component and configured to provide motive power to the flight component, and the second electric motor is able to provide motive power to the flight component if the first electric motor is inoperative.

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: 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 for distributed flight controllers for an electric aircraft is provided. The system includes a plurality of flight components coupled to the electric aircraft, a first controller coupled to an electric aircraft, the first controller configured to receive a plurality of measured aircraft data and generate a controller allocation datum as a function of the plurality of measured aircraft data. The system further includes a plurality of second controllers, wherein each second controller is configured to receive the controller allocation datum from the first controller, generate an allocation command as a function of the controller allocation datum, and provide the allocation command to each flight component of the plurality of flight components.

Abstract: A system for dynamic excitation of an energy storage element configured for use in an electric aircraft includes a plurality of propulsors mechanically connected to the electric aircraft. The system includes a plurality of energy storage elements electrically connected to the plurality of propulsors. The system includes a bus element, wherein the bus element is electrically connected to the plurality of energy storage elements and a cross tie element connected to the bus element configured to disconnect a first energy storage element from a second energy storage element. The system includes a modulator unit electrically connected to the bus element configured to modulate a first electrical command to the first energy storage element and a second electrical command to the second energy storage element. The system includes at least a sensor configured to detect an energy datum corresponding to the first energy storage element as a function of the modulation.