Abstract: A system for flight control configured for use in an electric aircraft 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, perform a torque allocation as a function of the moment datum, and generate a motor command datum as a function of the torque allocation.

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, a propulsor gauge is provided that provides guidance during a transition of a mode of operation of an electronic aircraft. Propulsor gauge may include a processor configured to identify a current thrust envelope parameter of one or more propulsors of electric aircraft. Processor may also determine a recommended range as a function of the propulsor parameter, where the recommended range includes a lower threshold and an upper threshold. The recommended range and thrust envelope parameter may then be shown on a display of propulsor gauge, where a measurement of current thrust envelope parameter relative to recommended range may be represented by an indicator.

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 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 fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.

Abstract: In an aspect, a propulsor gauge is provide that provides guidance during a transition of a mode of operation of an electric aircraft. Propulsor gauge may include a processor configured to identify a current thrust envelope parameter of one or more propulsors of electric aircraft. Processor may also determine a recommended range as a function of the propulsor parameter, where the recommended range includes a lower threshold and an upper threshold. The recommended range and thrust envelope parameter may then be shown on a display of propulsor gauge, where a measurement of current thrust envelope parameter relative to recommended range may be represented by an indicator.

Abstract: Aspects relate to augmented reality (AR) methods and systems for simulated operation of an electric vertical take-off and landing (eVTOL) aircraft. An exemplary AR system includes at least an aircraft component of an eVTOL aircraft, a computing device configured to operate a flight simulator to simulate flight in an environment and simulate at least a virtual representation interactive with the flight simulator, where the at least a virtual representation includes an aircraft digital twin of the at least an aircraft component, and a mesh network configured to communicatively connect the at least an aircraft component and the computing device and communicate encrypted data.

Abstract: Systems and methods for flight control on an electric aircraft. The system includes a propulsor configured to generate lift to propel an electric aircraft, a pilot input mechanically coupled to the electric aircraft, a sensor communicatively connected to the pilot input, and a flight controller communicatively connected to the sensor. Sensor is configured to detect an input datum from the pilot input and convert the input datum into a command datum for the propulsor as a function of input mapping. Input mapping is determined as a function of the phase of flight.

Abstract: A system for distributed pilot control of an aircraft includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components. The aircraft component may be configured to receive, from a command sensor attached to the aircraft control, an aircraft command. The aircraft component may further be configured to obtain, from an attitude sensor, an aircraft orientation. The aircraft component may further be configured to command the flight component to produce a response command as a function of a pilot signal.

Abstract: A system for the prioritization of flight controls in an electric aircraft is illustrated. The system includes a plurality of flight components, a sensor, and a computing device. The plurality of flight components are coupled to the electric aircraft. The sensor is coupled to each flight component of the plurality of flight components. Each sensor of the plurality of sensors is configured to detect a failure event of a flight component of the plurality of flight components and generate a failure datum associated to the flight component of the plurality of flight components. The computing device is communicatively connected to the sensor and is configured to receive the failure datum associated to the flight component of the plurality of flight component from the sensor, determine a prioritization element as a function of the failure datum, and restrict at least a flight element as a function of the prioritization element.

Abstract: A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

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 and a method for controlling a propulsor assembly of an electric aircraft. The system may include an electric motor, wherein the electric motor may include a rotor and a stator, a propulsor driven by the electric motor configured to propel an electric aircraft. The propulsor may include a propeller. The propeller may include a blade. The system may include a cyclic control assembly configured to deflect the blade. The cyclic control assembly may include an actuator and a push rod mechanically connected to the actuator and the propulsor. The system may include a flight controller. The flight controller may be configured to receive sensor datum from at least a sensor communicatively connected to the electric aircraft, generate a deflection command as a function of the sensor datum and actuate the cyclic control assembly as a function of the deflection command.

Abstract: A lift lever assembly for a vertical takeoff and landing (VTOL) aircraft is disclosed. The assembly includes a lever configured to control a lift propulsor of an aircraft. The assembly additionally includes at least a handle mechanically coupled to the lever, wherein the handle configured to allow transition of the lever from a thrust-engaged position to a thrust-disengaged position when the at least a handle is in an active position. The assembly also includes at least a sensor in communication with the lever, wherein the at least a sensor is configured to identify when the lever transitions from the thrust-engaged position to the thrust-disengaged position.

Abstract: A system for pilot-controlled position guidance configured for use in a vertical take-off and landing (VTOL) aircraft, the system including a VTOL aircraft. The system including a graphical user interface (GUI) coupled to the VTOL aircraft, where the GUI is configured to receive an objective from a user as a function of the user's interaction with the GUI, transmit the objective to a controller, receive a control input from the controller, and display the control input to the user. The system also including a controller where the controller is configured to receive the objective for the GUI, calculate a control input as a function of the objective, and transmit the control input to the GUI.

Abstract: Aspects relate to method and systems for simulated intra-aircraft communication using a physical network. An exemplary method includes receiving simulator data from an aircraft simulator, disaggregating a simulated digital message from the simulator data, abstracting a simulated signal as a function of the simulated digital message, transmitting the simulated signal on a physical network, receiving, using at least an aircraft component communicative with the physical network, the simulated signal by way of the physical network, transmitting a phenomenal signal by way of the physical network, receiving the phenomenal signal by way of the physical network, converting a phenomenal digital message as a function of the phenomenal signal, and inputting the phenomenal digital message to the aircraft simulator.

Abstract: A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.

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: A system of an electric aircraft with pitch control using an elevator is presented. In some embodiments, the electric aircraft may include an elevator configured to deflect. In some embodiments, the electric aircraft may further include a lift lever configured to generate a lift command upon activation by a pilot. In some embodiments, the electric aircraft may further include a flight controller communicatively connected with the lift lever and the elevator, wherein the flight controller is configured to receive the lift command from the lift lever and adjust the elevator as a function of the lift command.