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: 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: 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: A system for charging an electric aircraft. The system includes an electric aircraft port, at least a current conductor, a power supply circuit and a controller. The electric aircraft port is configured to mate with a charging connector. At least a portion of the at least a current conductor is at the electric aircraft port. The at least a current conductor is configured to conduct a charging current to at least an energy source of the electric aircraft. The power supply circuit is electrically connected to the at least a current conductor. The power supply circuit is configured to regulate the charging current supplied to the at least an energy source. The controller is communicatively connected to the power supply circuit. The controller is configured to control operation of the power supply circuit as a function of a power threshold. A method for charging an electric aircraft is also provided.

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: System and method for determining distance in navigation of an electric aircraft is illustrated. The system and method comprise a sensor and a computing device. The sensor is configured to detect a surface and transmit at least a first signal and a first frequency and at least a second signal at a second frequency to a computing device, wherein the first signal and the second signal comprise a corresponding distance. The computing device is configured to receive a returned signal from the sensor, wherein the returned signal comprises an intermodulation product associated to the first signal and the second signal, detect an amplitude of the returned signal as a function of the frequency, identify a distance datum as a function of the amplitude and an amplitude threshold, determine an aircraft adjustment as a function of the distance datum, and transmit the distance datum and aircraft adjustment to a remote device.

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: In an aspect, a system for recharging an electric vehicle. A system includes an electric vehicle. An electric vehicle includes at least a propulsor. An electric vehicle includes a recharging connector electrically connected to a power source. An electric vehicle includes a power storage unit. A power storage unit is configured to store power. An electric vehicle includes a power supply circuit. A power supply circuit is in electric communication with a power storage unit and recharging connector. A power supply circuit includes a buck-boost regulator. A buck-boost regulator includes at least an inductor. A buck-boost regulator includes a switching device to supply intermittent current to at least an inductor. At least one of at least an inductor and a switching device is a component of at least a propulsor motor.

Abstract: A system for flight control system using simulator data for an electric aircraft is presented. The system includes a computing device, the computing device configured to receive a plurality of measured flight data, simulate a plurality of aircraft performance model outputs as a function of a flight simulator and the plurality of measured flight data, determine a moment datum as a function of the plurality of measured flight data and the plurality of aircraft performance model outputs, generate an allocation command datum as a function of the moment datum and the plurality of aircraft performance model outputs, and perform a torque allocation on a flight component of a plurality of flight components as a function of the allocation command and the moment datum.

Abstract: A connector for charging an electric vehicle that includes a housing configured to mate with an electric vehicle port of an electric vehicle, at least a sensor configured to detect an attachment datum as a function of the housing mating with an electric vehicle port, and transmit the attachment datum to a computing device, a computing device configured to receive the attachment datum from the at least a sensor, receive an identification datum from the electric vehicle, generate a verification datum as a function of the identification datum and the attachment datum, and determine an authorization status as a function of the verification datum.

Abstract: In an aspect, a system includes a plurality of propulsors connected to an aircraft. Each propulsor of the plurality of propulsors is configured to operate independently from one another. A system includes a fuselage of an aircraft. A fuselage is configured to include a protective barrier and a height greater than the plurality of propulsors. A system includes a plurality of electric motors configured to adjust a torque of each propulsor of the plurality of propulsors. A system includes a computing device configured to detect a torque of each propulsor of the plurality of propulsors. A computing device is configured to determine a flight maneuver. A computing device is configured to adjust a property of each propulsor of the plurality of propulsors using the plurality of electric motors as a function of the detected torque.

Abstract: Aspects relate to a connector and methods of use for charging an electric vehicle. An exemplary connector includes a housing configured to mate with an electric vehicle port of an electric vehicle, where the housing includes a fastener for removable attachment with the electric vehicle port, at least a direct current conductor configured to conduct a direct current, at least an alternating current conductor, configured to conduct an alternating current, 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 coolant flow path 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 vehicle port when the housing is mated with the electric vehicle port.

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 connector for charging an electric vehicle that includes a housing configured to mate with an electric vehicle port of an electric vehicle, at least a sensor configured to detect an attachment datum as a function of the housing mating with an electric vehicle port, and transmit the attachment datum to a computing device, a computing device configured to receive the attachment datum from the at least a sensor, receive an identification datum from the electric vehicle, generate a verification datum as a function of the identification datum and the attachment datum, and determine an authorization status as a function of the verification datum.

Abstract: A system for automated flight correction is an electric aircraft that includes an input control configured to receive a user input and generate a control datum as a function of the user input, at least a sensor connected to the electric aircraft that is configured to detect a status datum and transmit the status datum to a flight controller, a flight controller communicatively connected to the input control and the at least a sensor configured to receive the control datum from the input control, receive the status datum from the flight controller and determine a command datum as a function of the control datum and status datum, and an actuator connected to the flight controller configured to receive the command datum from the flight controller and command at least a flight component as a function of the command datum.

Abstract: A system for estimating the angular position of a rotating shaft in an aircraft, the system including at least three electromagnetic effect sensors. The system including a flight controller that runs a voting algorithm, wherein the voting algorithm computes an output datum based on shaft position datum that qualify as both active and admissible. Furthermore, system may include, as a component of the voting algorithm, a banning process where sensors that repeatedly return datum that are either not active or not admissible can be banned.

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: 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 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 distributed flight control configured for use in an electric vehicle wherein the system includes a flight control assembly which further includes at least a sensor electronically connected to the flight control assembly. The sensor is configured to capture at least an input datum, and at least a performance datum. The system further includes a plurality of modular flight controllers communicatively coupled to at least an actuator of a plurality of actuators, wherein each modular flight controller of the plurality of modular flight controllers is configured to the multitude of data from at least a sensor, generate an attitude control datum, determine at least an actuator instruction datum, and perform a control allocation configured for the at least a actuator from the plurality of actuators to follow as a function of the flight control assembly.