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: Abstract of the Disclosure: In an aspect systems and methods for monitoring health of an electric vertical take-off and landing vehicle include at least a flight component, a first sensor, a computing device, and a pilot display. The first sensor is configured to sense a first characteristic associated with the at least a flight component and transmit the first characteristic. The computing device is communicative with the first sensor, and is configured to: receive the first characteristic, analyze the first characteristic, and determine a condition of the at least a flight component as a function of the first characteristic. The pilot display is communicative with the first sensor and the computing device and is configured to: receive the first characteristic and the condition of the at least a flight component and display the first characteristic and the condition of the at least a flight component.

Abstract: In an aspect systems and methods for monitoring health of an electric vertical take-off and landing vehicle include at least a flight component, a first sensor, a computing device, and a pilot display. The first sensor is configured to sense a first characteristic associated with the at least a flight component and transmit the first characteristic. The computing device is communicative with the first sensor, and is configured to: receive the first characteristic, analyze the first characteristic, and determine a condition of the at least a flight component as a function of the first characteristic. The pilot display is communicative with the first sensor and the computing device and is configured to: receive the first characteristic and the condition of the at least a flight component and display the first characteristic and the condition of the at least a flight component.

Abstract: An electric aircraft having fixed pitch lift includes a plurality of flight components, 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 an angle of attack, and a flight controller, wherein the flight controller is configured to calculate a flight element using an intermediate representation, and transmit the flight element to the plurality of flight components.

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: 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.