A system for automated flight correction is an electric aircraft that includes an input control configured to receive a user input and generate a control datum as a function of the user input, at least a sensor connected to the electric aircraft that is configured to detect a status datum and transmit the status datum to a flight controller, a flight controller communicatively connected to the input control and the at least a sensor configured to receive the control datum from the input control, receive the status datum from the flight controller and determine a command datum as a function of the control datum and status datum, and an actuator connected to the flight controller configured to receive the command datum from the flight controller and command at least a flight component as a function of the command datum.

A system for automated flight correction is an electric aircraft that includes an input control configured to receive a user input and generate a control datum as a function of the user input, at least a sensor connected to the electric aircraft that is configured to detect a status datum and transmit the status datum to a flight controller, a flight controller communicatively connected to the input control and the at least a sensor configured to receive the control datum from the input control, receive the status datum from the flight controller and determine a command datum as a function of the control datum and status datum, and an actuator connected to the flight controller configured to receive the command datum from the flight controller and command at least a flight component as a function of the command datum.

The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.

The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.

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.

An assembly for manual control of an HSTA for controlling the position of a moveable surface, the assembly comprising a user-operated manual control element (1′) e.g. a trim wheel in the cockpit, a first motor and a first resolver connected to the manual control element and a second motor and a second resolver arranged to communicate with the first motor and the first resolver and to cause corresponding movement of the actuator, in use.

An assembly for manual control of an HSTA for controlling the position of a moveable surface, the assembly comprising a user-operated manual control element (1′) e.g. a trim wheel in the cockpit, a first motor and a first resolver connected to the manual control element and a second motor and a second resolver arranged to communicate with the first motor and the first resolver and to cause corresponding movement of the actuator, in use.

Methods and systems for providing reduced flaps takeoff or landing advice in an aircraft. The methods and systems include a display device and a processor in operable communication with the display device. The processor is configured to execute program instructions. The program instructions are configured to cause the processor to receive takeoff or landing performance data including weather data and runway conditions data for a plurality of runways at a destination aerodrome, calculate values of takeoff or landing performance parameters for a plurality of flap configurations for each of the plurality of runways, and present, on the display device, at least one of the values of takeoff or landing performance parameters.

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.

A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a fuselage, a plurality of laterally extending elements, a plurality of propulsors, a flight controller, and a pilot override switch. The plurality of laterally extending elements are attached to the fuselage. The plurality of propulsors is attached to the plurality of laterally extending elements. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a flight transition point, initiate rotation about an axis of the fuselage a as function of the flight transition point, and terminate rotation once the desired flight angle is reached.