Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for command prioritization in an aircraft is disclosed. The method comprises receiving a pilot command, analyzing the pilot command to determine characteristics associated with the pilot command, wherein the characteristics to airspeed and climb of an aircraft, assigning weights to characteristics associated with the pilot command based on constraint data, determining priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command, calculating a correction factor to be applied to the characteristics associated with the pilot command based on determined priority and generating at least one actuator command to control the aircraft based on determined priority of execution.

A system for controlling a flight boundary of an aircraft. The system includes a flight controller communicatively connected to the aircraft. The flight controller is configured to receive a plurality of flight data linked with the aircraft, determine a flight boundary for the aircraft as a function of the plurality of flight data, set an aircraft movement limit as a function of the flight boundary, receive a thrust envelope, and generate a control signal for the aircraft as a function of the aircraft movement limit and the thrust envelope. The control signal is limits the aircraft to remain within the flight boundary. A method for controlling a flight boundary of an aircraft is also provided.

Disclosed embodiments generally relate to systems and methods for flight control of aircrafts. In some embodiments, a flight control system is configured to determine desired commands for the electric aircraft, determine at least one reference command for an effector based on the desired commands and one or more aircraft conditions, monitor energy states of the plurality of battery packs, where at least a first battery pack of the plurality of battery packs is electrically isolated from at least a second battery pack of the plurality of battery packs, adjust the at least one reference command based on the monitored energy states of the plurality of battery packs, generate control commands for the plurality of effectors based on the adjusted at least one effector reference command, and control the plurality of effectors according to the generated control commands to meet the one or more desired commands of the electric aircraft.

A craft comprises at least one hull; at least one wing configured to generate upwards aero lift as air flows past the at least one wing to facilitate wing-borne flight of the craft; a front hydrofoil connected to the at least one hull via a front hydrofoil strut and configured to generate upward hydrofoil lift as water flows past the front hydrofoil to facilitate hydrofoil-borne movement of the craft through the water; a rear hydrofoil connected to the at least one hull via a rear hydrofoil strut and configured to generate upward hydrofoil lift as water flows past the rear hydrofoil to facilitate hydrofoil-borne movement of the craft through the water; and a control system. While the craft is hydrofoil-borne, the control system is configured to facilitate transition of the craft from hydrofoil-borne operation to wing-borne operation via a process comprising: while the upwards aero lift generated by the at least one wing is below a threshold lift, controlling one or both of the front hydrofoil and the rear hydrofoil to generate a downward hydrofoil lift that causes the front hydrofoil and the rear hydrofoil to remain at least partially submerged in the water; and after the upwards aero lift generated by the at least one wing has increased above the threshold lift, transitioning the craft from hydrofoil-borne operation to wing-borne operation at least in part by controlling one or both of the front hydrofoil and the rear hydrofoil to switch from (a) generating the downward hydrofoil lift to (b) generating an upward hydrofoil lift that pushes the craft up and out of the water.

A computer-implemented method of enabling optimisation of trajectory for a vehicle, the method comprising: determining a trajectory for the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of a propulsion system of the vehicle; an objective function defining one or more objectives; and controlling output of the determined trajectory.

An information processing method, performed by a computer, includes: obtaining second situational information related to a situation of at least one of a vehicle or surroundings of the vehicle at a second time point subsequent to a first time point; determining recommended content related to vehicle monitoring recommended to a second monitoring agent by inputting the second situational information to a trained model obtained by machine learning in which first situational information and a first monitoring result which is a result of monitoring by a first monitoring agent based on the first situational information are used, the first situational information being related to a situation of at least one of the vehicle or the surroundings of the vehicle at the first time point; generating presentation information for vehicle monitoring based on the recommended content determined; and causing a presentation device to output the presentation information.

Provided are methods for route traversal using remote vehicle assistance, which can include a method. The method includes: identifying a condition on a route traveled by a vehicle that inhibits movement of the vehicle along the route; sending an assistance request to a remote operator; receiving an updated trajectory for the vehicle to travel along the route, the updated trajectory including one or more segments; evaluating whether the vehicle can be controlled to safely traverse a first segment with a safe stop upon completion of traversal of the first segment; determining that the vehicle can be controlled to safely traverse the first segment with a safe stop; and upon determining that the vehicle can be controlled to traverse the first segment with a safe stop upon completion of the traversal of the first segment, controlling the vehicle to traverse the first segment. Systems and computer program products are also provided.

A flight control system for an aircraft including a first set of primary flight control computers and a second set of secondary flight control computers, where each primary flight control computer implements a first autopilot functionality. The secondary flight control computers jointly take control of control surface actuators when the primary flight control computers fail. The flight control system further includes another computer, to which the secondary flight control computers are connected, which implements a simplified second autopilot functionality, the second autopilot functionality being able to be activated only when the second set of flight control computers has control of the control surface actuators. Thus, an autopilot functionality is widely available, while at the same time ensuring the robustness sought by the installation of the secondary flight control computers.

A remote operator terminal to be used by a remote operator for a remote operation of a target mobility is provided. The remote operator terminal includes: a plurality of types of operation systems; and a first user interface configured to allow the remote operator to select a first operation system to be used for the remote operation from among the plurality of types of operation systems.

A remote operator terminal to be used by a remote operator for a remote operation of a target mobility is provided. The remote operator terminal includes a plurality of types of operation systems, a user interface, and a processing circuitry configured to perform calibration of a target operation system among the plurality of types of operation systems. In the calibration, the processing circuitry presents a first notification to the remote operator through the user interface, the first notification prompting the remote operator to perform a first action on the target operation system. Then, the processing circuitry sets a zero point of the target operation system based on a content of the first action or a state of the target operation system during the first action.