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.

Actuator for moving an aircraft control part, the actuator comprising: a mobile element movable in a first direction and in a second direction; an actuating means for moving the mobile element (2); a mechanical brake which, in case of loss of electrical power and/or in case of a brake signal, brakes the mobile element in the first direction until a force from the aircraft control part on the mobile element (2) exceeds a threshold force.

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.

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.

A Stability and Control Augmentation System (“SCAS”) module comprising one or more SCAS actuators, the or each SCAS actuator comprising a mechanical component that translates rotational motion to linear motion along a first axis of said SCAS; one or more electric motors for driving linear movement of the mechanical component in response to a command signal; and one or more angular transducers to detect the position of the SCAS actuator along the first axis.

A system for automated flight correction in an electric aircraft includes an input control configured to generate a control datum, at least a sensor connected to the electric aircraft, wherein the at least a sensor is configured to detect a status datum, and a flight controller communicatively connected to the input control and the at least a sensor, wherein the flight controller is configured to determine a command datum as a function of the control datum and the status datum, wherein determining the command datum comprises comparing the control datum to a limitation set based on the status datum, and calculating a modified control datum based on a flight plan of the electric aircraft through a remote device.

Aircraft, fly-by-wire systems, and controllers are provided. An aircraft includes a trim control system and a fly-by-wire system. The trim control system is configured for controlling surfaces of the aircraft. The fly-by-wire system is communicatively coupled with the trim control system and includes an input device and a controller. The input device is configured to receive a re-trim input from a user. The controller is communicatively coupled with the input device and is configured to control the trim control system, to obtain the re-trim input from the user, and to set a pitch trim of the aircraft based on a stable flight condition at a present airspeed of the aircraft in response to the re-trim input from the input device.

A system of fall back flight control configured for use in aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

One example aspect of the present disclosure relates to a method for assessing input. The method can include determining a state of the aerial vehicle. The method can include obtaining data indicative of an expected operator input based on the determined state. The method can include obtaining data indicative of an actual operator input. The method can include determining a state of operator behavior based on the expected operator input and the actual operator input. The method can include determining a control action for the aerial vehicle based on the determined state of the aerial vehicle and the determined state of the operator behavior. The method can include implementing the control action.

Systems and methods according to one or more embodiments are provided for limiting elevator deflection commands to avoid the aft body of an aircraft from contacting the ground during a landing maneuver. In one example, a system includes a memory configured to store a plurality of executable instructions and a processor. The processor is configured to determine a descent profile and a current pitch profile. A pre-determined maximum pitch profile associated with the descent profile is used to compare to the current pitch profile. The comparison is used to compute an elevator deflection value that limits an elevator command signal in order to avoid a tail strike. Additional systems and methods are also provided.