Abstract: A method of in-flight operational assessment for an electric aircraft comprising detecting by a sensor an electrical parameter of an energy source. The method further includes receiving by a controller the electrical parameter from the sensor and determining a power-production capability of the energy source, using the electrical parameter. The method further includes calculating, by the controller, a projected power-consumption need of the electric aircraft and comparing the determined power-production capability of the energy source to the projected power-consumption need. The method includes generating a power production command datum as a function of the comparison of the power-production capability and the projected power-consumption need.

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: Aspects of the present disclosure include an aircraft with auxiliary components that are powered by an external power supply. Auxiliary components may include components that are used while the aircraft is grounded. Auxiliary components may be off while the aircraft is in flight.

Abstract: Aspects of the present disclosure include an aircraft with auxiliary components that are powered by an external power supply. Auxiliary components may include components that are used while the aircraft is grounded. Auxiliary components may be off while the aircraft is in flight.

Abstract: Various techniques are provided to assemble, manufacture, and use a power source. A power source assembly system is provided to apply a compressive force on a plurality of battery cells so that the battery cells may be inserted into a compact container without damaging the battery cells.

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 system and method for the overcurrent protection in an electric vehicle is illustrated. The system comprises an electric vehicle charging port that includes an AC pin, a DC pin, a sensor, and a controller. The electric vehicle charging port also includes a protection circuit, wherein the protection circuit is configured to control a transmission of power through the electric vehicle charging port.

Abstract: Aspects relate to an electric vehicle port and methods of use for charging an electric vehicle. An exemplary electric vehicle port includes a housing configured to mate with a connector for charging an electric vehicle, wherein the housing comprises a fastener for removable attachment with the connector; at least a conductor configured to conduct a current; at least a control signal conductor configured to conduct a control signal; at least a ground conductor configured to conduct to a ground; and at least a coolant flow path configured to contain a flow of a coolant, wherein, each of the at least a conductor, the at least a control signal conductor, the at least a ground conductor, and the at least a coolant flow path are configured to make a connection with a mating component on the connector for charging the electric vehicle when the housing is mated with the connector.

Abstract: In an aspect, a modular battery configuration with a centralized bus on an electric aircraft, including an electric aircraft which comprises a propulsor configured to generate thrust and a centralized electrical bus connected to the propulsor. A plurality of modular battery packs is configured to provide electricy to the centralized electrical bus, wherein the plurality of modular battery packs is arranged about a center of gravity of the electric aircraft.

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: 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 pilot, 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 pilot. 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: In an aspect a connector for charging an electric vehicle. A connector includes a coupling mechanism. A coupling mechanism is configured to mate with an electric vehicle port of an electric vehicle. A coupling mechanism includes a fastener for removable attachment with an electric vehicle port. A connector includes at least a direct current conductor. At least a direct current conductor is configured to supply a direct current to an electric vehicle. A connector includes a power supply circuit. A power supply circuit is configured to regulate a direct current supplied to an electric vehicle as a function of a power threshold.

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 thrust envelope, and generate a control signal for the aircraft as a function of the aircraft movement limit and the thrust envelope. 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: An electric vehicle charging connector, including a set of pins, a sensor, and a controller. The set of pins may include a DC pin, wherein the DC pin is configured to supply DC power to a charging port, wherein the charging port comprises a locking mechanism. 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 comprises 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, wherein the locking mechanism is configured to receive a locking signal from the controller of the charging connector and enter the engaged state.

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: An apparatus for determining a resource remaining datum of an electric aircraft is disclosed. The apparatus includes a processor and a memory communicatively connected to the processor. The memory contains instructions configuring the processor to receive aircraft data from at least a sensing device, wherein the at least a sensing device is configured to measure at least a parameter of a battery pack of the electric aircraft and generate aircraft data as a function of the at least a parameter of the battery pack of the electric aircraft. The memory contains instructions configuring the processor to determine a reserve energy as a function of a flight mode of the electric aircraft and determine a resource remaining datum as a function of the aircraft data and the reserve energy, wherein the resource remaining datum is related to the battery pack of the electric aircraft.

Abstract: A system for determining remaining useful energy in an electric aircraft, the system including a computing device where the computing device is configured to measure a internal state datum of a battery as a function of at least a sensor, receive the internal state datum from the at least a sensor, generate a useful energy remaining datum as a function of the internal state datum and a battery model, and display the useful energy remaining datum to a user.

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: The system and method for defining boundaries of a simulation of an electric aircraft is illustrated. The system comprises a sensor, a computing device, and a remote device. The sensor is configured to detect an aircraft location datum, detect a boundary datum associated with a three-dimensional flying space, and transmit the aircraft location datum and boundary datum to a computing device. The computing device is configured to receive the aircraft location datum and boundary datum from the sensor, determine a distance datum between the aircraft location and boundary as a function of the aircraft location datum and boundary datum generate a recommended aircraft adjustment as a function of the distance datum, and transmit the distance datum and recommended aircraft adjustment to a remote device. The remote device is configured to receive the distance datum and recommended aircraft adjustment and display them to a user.

Abstract: An electric vehicle charging connector including a charging connector. The charging connector including a direct current pin and an alternating current pin. The electric vehicle charging connector also including a coupling mechanism configured to: couple the charging connector to an electric vehicle, enable a flow of electricity from the charging connector to the electric vehicle, and disable the flow of electricity from the charging connector to the electric vehicle.