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 virtualizing a plurality of controller area network bus units communicatively connected to an aircraft, the system comprising a plurality of physical controller area network bus units, each is configured to detect a measured state datum of a plurality of measured state data of the aircraft; and transmit the plurality of measured state data to at least a network switch, the at least a network switch configured to receive the plurality of measured state data from the plurality of physical controller area network bus units, generate a single transmission signal as a function of the plurality of measured state data, and transmit the single transmission signal to a computing device, and the computing device configured to receive the transmission signal originating from the at least a network switch, and bridge each virtual controller area network bus unit of the plurality of virtual controller area network bus units.

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, 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 for virtualizing a plurality of controller area network bus units communicatively connected to an aircraft, the system comprising a plurality of physical controller area network bus units, each is configured to detect a measured state datum of a plurality of measured state data of the aircraft; and transmit the plurality of measured state data to at least a network switch, the at least a network switch configured to receive the plurality of measured state data from the plurality of physical controller area network bus units, generate a single transmission signal as a function of the plurality of measured state data, and transmit the single transmission signal to a computing device, and the computing device configured to receive the transmission signal originating from the at least a network switch, and bridge each virtual controller area network bus unit of the plurality of virtual controller area network bus units.

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: Some aspects relate to systems and methods for fly-by-wire reversionary flight control including a pilot control, a plurality of sensors configured to: sense control data associated with the pilot control, and transmit the control data, a first actuator communicative with the plurality of sensors configured to receive the control data, determine a first command datum as a function of the control data and a distributed control algorithm, and actuate a first control element according to the first command datum.

Abstract: An aircraft for fixed pitch lift includes a fuselage, a plurality of flight components attached to the fuselage, wherein the plurality of flight components further comprises at least a lift propulsor component, wherein the lift propulsor component comprises a plurality of blades configured at a fixed angle of attack, and a pusher component, wherein the pusher component is configured to produce a forward thrust.

Abstract: A system for virtualizing a plurality of controller area network bus units includes a plurality of physical controller area network buses communicatively connected to an aircraft, each configured to detect a measured state datum of a plurality of measured state data of the aircraft, a plurality of controller area network gateways communicatively connected to the plurality of physical controller area network buses, wherein the plurality of controller area network gateways are configured to transmit the plurality of measured state data, at least a network switch communicatively connected to the plurality of controller area network gateways configured to receive the transmitted measured state data, and transmit the measured state data via a single transmission signal, and at least a virtual controller area network bus unit configured to receive the single transmission signal originating from the at least a network switch and bridge a plurality of virtual controller area network bus units.