Abstract: An electric aircraft with flight trajectory planning. The electric aircraft includes a sensor. The sensor is coupled to the electric aircraft. The sensor is configured to detect a plurality of weather measurements. The electric aircraft includes a processor. The processor is communicatively connected to the sensor. The processor is configured to receive, from the sensor, a weather measurement of the plurality of weather measurements. The processor is configured to receive, from a user, a destination datum and a desired altitude datum. The processor is configured to determine an optimal trajectory of the electric aircraft as a function of the destination datum, weather datum, and altitude 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: An electric aircraft for generating a yaw force includes a fuselage, a plurality of laterally extending elements secured to the fuselage, a plurality of lift components attached to the plurality of laterally extending elements, and at least a longitudinal thrust component attached to the plurality of laterally extending elements, wherein the longitudinal thrust component is configured to generate a yaw force.

Abstract: In an aspect, a system for a guidance interface for a vertical take-off and landing (VTOL) aircraft comprises a plurality of flight components that are mechanically coupled to the VTOL aircraft. The VTOL aircraft also comprises an output device that is configured to present a display of the outside environment. The output device may overlay the display with a datum, a focal point, and a guidance symbol. The datum may be associated with the flight components of the VTOL aircraft. The focal point may be indicative of a desired landing location for the VTOL aircraft. The focal point may be determined by at least a predetermined flight plan. The guidance symbol may be a symbol that includes an optimal flight path to the focal point.

Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.

Abstract: An aircraft for vectoring a plurality of propulsors includes a longitudinal component attached to a fuselage, a plurality of downward directed propulsors attached to a plurality of laterally extending elements secured to the fuselage, a sensor attached to the plurality of downward directed propulsors, a flight controller, wherein the flight controller is configured to receive a flight datum as a function of the sensor, and vector the plurality of downward directed propulsors along a boom axis as a function of the flight datum.

Abstract: A system for electric aircraft navigation includes a sensor configured to detect a navigation signal, a flight controller, wherein the flight controller is configured to receive the navigation signal, identify a navigation status as a function of the navigation signal, and determine an aircraft adjustment as a function of the navigation status, and a pilot display, wherein the pilot display is configured to display the aircraft adjustment to a user, and present an autonomous function configured to enact the aircraft adjustment automatically.

Abstract: An electric aircraft with flight trajectory planning. The electric aircraft includes a sensor. The sensor is coupled to the electric aircraft. The sensor is configured to detect a plurality of weather measurements. The electric aircraft includes a processor. The processor is communicatively connected to the sensor. The processor is configured to receive, from the sensor, a weather measurement of the plurality of weather measurements. The processor is configured to receive, from a user, a destination datum and a desired altitude datum. The processor is configured to determine an optimal trajectory of the electric aircraft as a function of the destination datum, weather datum, and altitude datum.

Abstract: A system and method for pilot assists of an electric vertical takeoff and landing (eVTOL) aircraft. The system generally includes a pilot control and a flight controller. The pilot control is attached to the eVTOL aircraft. The pilot control is configured to transmit an input relating to the flight path of the aircraft. The flight controller is communicatively connected to the pilot control. The flight controller is configured to receive the input relating to the flight path, generate an output of a recommended flight maneuver as a function of the input, and display the recommended flight maneuver.

Abstract: A system for flight control of a vertical take-off and landing (VTOL) aircraft includes a flight simulator communicatively coupled to a VTOL aircraft, wherein the flight simulator is configured to generate a model for at least a flight component and a flight controller, wherein the flight controller is configured to receive the model for the at least a flight component, determine a command for the at least a flight component as a function of the model, and initiate the command for the at least a flight component.

Abstract: A command model connected to plurality of flight components of an electric aircraft and comprises a circuitry configured to detect a predicted state and a measured state datum, transmit predicted state datum to an actuator model, and transmit measured state datum to a plant model. An actuator model connected to the sensor configured to receive the predicted state datum and generate a performance datum. A plant model connected to the sensor configured to receive measured state datum and performance datum from the actuator model, transmit a feedback path to controller, and generate an inconsistency datum as a function of the measured state datum and the performance datum. A controller communicatively connected to the sensor, wherein the controller is configured to receive the inconsistency datum from the plant model and apply a torque to the aircraft as a function of the inconsistency datum.

Abstract: A system for electric aircraft navigation includes a sensor configured to detect a navigation signal, a flight controller, wherein the flight controller is configured to receive the navigation signal, identify a navigation status as a function of the navigation signal, and determine an aircraft adjustment as a function of the navigation status, and a pilot display, wherein the pilot display is configured to display the aircraft adjustment to a user, and present an autonomous function configured to enact the aircraft adjustment automatically.

Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.