Abstract: A system and method for speed control as a function of battery capability in an electric aircraft is illustrated. The system comprises a battery pack coupled to the electric aircraft, a sensor coupled to the battery pack and configured to detect a battery pack output, and a computing device coupled to the sensor. The computing device is configured to receive the battery pack output from the sensor and adjust a maximum speed of the electric aircraft as a function of the battery pack output and a battery pack output threshold.

Abstract: In an aspect of the present disclosure a pilot display system for an aircraft includes a sensor configured to measure an aircraft position and generate a position datum based on the aircraft position, a display incorporated in the aircraft, and a computing device communicatively connected to the sensor and the display, the computing device configured to receive a flight path including a transition point, determine, from the position datum, the aircraft position relative to the transition point, and command the display to display a visual representation of the aircraft position relative to the transition point.

Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a pusher component, a lift component, a flight controller, and a pilot override switch. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a transition point, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.

Abstract: A visual system for an electric vertical takeoff and landing (eVTOL) aircraft is illustrated. The system comprises an exterior visual device, a flight controller, and a pilot display. The exterior visual device is attached to the aircraft and is configured to detect an input of views of the exterior environment of the electric aircraft. The flight controller is communicatively connected to the aircraft, receives input from the exterior visual device, and generates an output of the view of the exterior environment of the aircraft as a function of the input. The pilot display is in the aircraft, receives the output of the view of exterior environment of the electric aircraft, and displays the output to a user.

Abstract: A system for flight control of an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control, a pusher component, a lift component and a flight controller. The pilot control is mechanically coupled to the eVTOL aircraft. The pilot control is configured to transmit an input datum. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input datum from the pilot control, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.

Abstract: A system for monitoring the landing zone of an electric aircraft, the system including an electric aircraft wherein the electric aircraft includes at least a sensor configured to measure a plurality of data of regarding a first potential landing zone and transmit the plurality of data to at least a flight controller. The flight controller is designed and configured to receive the plurality of data from at least a sensor, determine a landing safety datum as a function of the plurality of data and at least a safety parameter range, and transmit the landing safety datum to an output device. The output device is designed and configured to receive the plurality of data from the flight controller, and display, to the pilot, the landing safety datum and a locator component designed and configured to capture a second potential landing zone that is distinct from the first potential landing zone.

Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a pusher component, a lift component, a flight controller, and a pilot override switch. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a transition point, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.

Abstract: A system for flight control configured for use in an electric aircraft includes a sensor configured to capture an input datum. The system includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, map vehicle level control torques, received from the inner loop controller, to actuator output and generate a motor command datum as a function of the torque allocation.

Abstract: A system and method for speed control as a function of battery capability in an electric aircraft is illustrated. The system comprises a battery pack coupled to the electric aircraft, a sensor coupled to the battery pack and configured to detect a battery pack output, and a computing device coupled to the sensor. The computing device is configured to receive the battery pack output from the sensor and adjust a maximum speed of the electric aircraft as a function of the battery pack output and a battery pack output threshold.

Abstract: A system and method for the remote piloting of an electric aircraft is illustrated. The system comprises a remote device located outside an electric aircraft, wherein the remote device is configured to receive a flight command input from a user and transmit the flight command input to a flight controller located on the aircraft. The flight controller is located inside the aircraft and configured to receive the flight command input from the remote device and enact the flight command autonomously as a function of the flight command input.

Abstract: In an aspect of the present disclosure a pilot display system for an aircraft includes a sensor configured to measure an aircraft position and generate a position datum based on the aircraft position, a display incorporated in the aircraft, and a computing device communicatively connected to the sensor and the display, the computing device configured to receive a flight path including a transition point, determine, from the position datum, the aircraft position relative to the transition point, and command the display to display a visual representation of the aircraft position relative to the transition point.

Abstract: A system for monitoring sensor reliability in an electric aircraft is provided. The system includes a computing device communicatively connected to a first sensor and an electric aircraft. The first sensor is mechanically connected to the electric aircraft and is configured to detect a first flight datum of the electric aircraft. The computing device is configured to receive the first flight datum from the first sensor, compare the first flight datum to at least a corroboratory datum, and tag the first sensor as a function of the comparison of the first flight datum and the at least a corroboratory datum. A method for monitoring sensor reliability in an electric aircraft is also provided.

Abstract: A system and method for speed control as a function of battery capability in an electric aircraft is illustrated. The system comprises a battery pack coupled to the electric aircraft, a sensor coupled to the battery pack and configured to detect a battery pack output, and a computing device coupled to the sensor. The computing device is configured to receive the battery pack output from the sensor and adjust a maximum speed of the electric aircraft as a function of the battery pack output and a battery pack output threshold.

Abstract: A system for a head-up display for an electric aircraft is presented. The system includes an augmented reality device which may be operated by a pilot using a pilot device and a computing device connected to the pilot device, wherein the computing device is configured to receive an aircraft datum and generate a performance assessment model. The performance assessment model includes a plurality of information relevant to the operation of the electric aircraft. The augmented reality device further includes a projection device configured to project the performance assessment model onto an exterior view window and display the performance assessment model as a function of the projection device.

Abstract: Aspects relate to methods and systems for reversionary flight control for an electrical vertical take-off and landing (eVTOL) aircraft. An exemplary system includes a pilot control, a sensor configured to sense and transmit analog control data associated with a pilot interaction with the pilot control, a pilot interface module configured to receive the analog control data, convert the analog control data to digital control data, and transmit digital control, an actuator, and a flight controller. The flight controller may be configured to receive the digital control data, determine a primary command datum as a function of the digital control data, transmit the primary command datum to the actuator, determine that the digital control signal is non-functional, receive the analog control data, determine a reversionary command datum as a function of the analog control data, and transmit the reversionary command datum to the actuator.

Abstract: Systems and methods for lag optimization of pilot intervention is provided. A critical event may be identified while an electric aircraft is in an autopilot mode and operating primarily under autonomous functions; as a result, a flight controller of the system may switch from an autopilot mode to a manual mode, allowing pilot intervention. System made determine a lag duration as a function of the critical event and a phase of operation of the electric aircraft to determine a lag duration before pilot intervention occurs.

Abstract: In an aspect a system for fly-by-wire flight control configured for use in electric aircraft including at least a sensor, wherein the sensor is communicatively connected a pilot control and configured to detect a pilot input from the pilot control and generate, as a function of the pilot input, command datum. A system includes a flight controller, the flight controller including a computing device and configured to perform a voting algorithm, wherein performing the voting algorithm includes determining that the sensor is an allowed sensor, wherein determining that the sensor is an allowed sensor includes determining that the command datum is an active datum, determining the command datum is an admissible datum, generating, as a function of the command datum and the allowed sensor, a control surface datum wherein the control surface datum is correlated to the pilot input.

Abstract: A system for remote pilot control of an electric aircraft in autopilot mode including a remote computing device configured to receive a user input and generate a control datum as a function of the pilot input, a flight controller configured to receive the control datum from the remote computing device, and generate a command datum as a function of the control datum and an authority status, and the remote computing device configured to receive the command datum from the flight controller, and display the command datum.

Abstract: Provided in this disclosure are systems and methods for determining a confidence level of a sensor measurement of a sensor. A system may include a sensor array, which includes a plurality of sensors configured to detect a physical phenomenon. Each sensor of the sensor array may generate an output signal that includes measurement datum related to the detected physical phenomenon, which may be received by a controller of the system. Controller may compare the measurement datum from a selected sensor to other sensors of the sensor array to determine the confidence level of the selected sensor.

Abstract: A system and method for an automated sense and avoid system for an electric aircraft is illustrated. The system comprises a flight controller communicatively connected to an electric aircraft, wherein the flight controller is configured to receive a plurality of flight inputs from a sensor, determine an impact element as a function of the plurality of flight inputs, produce a flight modification as a function of the impact element, and initiate the flight modification as a function of an automated process.