A method and system for providing corrective action to a rotorcraft experiencing motor failure is provided. Included in the method and system are embodiments that receive feedback from sensors directed at measuring a state of motors used to provide lift to the rotorcraft. The method and system also describe embodiments for determining that there is a malfunctioning motor, and furthermore, the appropriate corrective action for responding to the malfunctioning motor. In some embodiments, the method and system are configured to reduce power to the malfunctioning motor while simultaneously adjusting power supplied to the remaining motors such that changes in total thrust and net torque are minimized.

An emergency module may determine the occurrence of an autorotation condition for a rotary wing air vehicle controlled by a user. The emergency module may, responsive to determining the occurrence of the autorotation condition, control the air vehicle to enter into an autorotation. The emergency module may perform one or more non-user actions during the autorotation to assist the user with the autorotation. The emergency module may, while performing the one or more non-user actions during the autorotation, allow the user to maneuver the air vehicle by interacting one or more control interfaces of the air vehicle.

An aerial vehicle, comprising: one or more motors, one or more sensors, and a flight sub-system. The one or more sensors configured to detect data. The flight sub-system includes an attitude controller module; a rate controller module; and a compensator module. The compensator module is configured to: determine a maximum RPM of the one or more motors or a maximum torque of the one or more motors; receive a torque vector from the rate controller module; determine a rotational speed of the one or more motors to generate a desired flight orientation based upon the torque vector; and consider sensor data from the one or more sensors to adjust the rotational speed of the one or more motors.

A flight control device performs a flight control process for causing an eVTOL to fly. In a step of the flight control process, the flight control device determines whether the eVTOL is capable of maintaining a stable attitude. In the step, it is determined whether the eVTOL is capable of maintaining the stable attitude even if driving of an abnormal motor is stopped. In the step, it is determined whether the eVTOL is capable of maintaining the stable attitude even if the abnormal motor continues driving. When it is determined that the eVTOL is capable of maintaining the stable attitude, the flight control device performs output adjustment of at least one of a normal motor and the abnormal motor to maintain the eVTOL at the stable attitude.

An aerial vehicle, comprising: one or more motors, one or more sensors, and a flight sub-system. The one or more sensors configured to detect data. The flight sub-system includes an attitude controller module; a rate controller module; and a compensator module. The compensator module is configured to: determine a maximum RPM of the one or more motors or a maximum torque of the one or more motors; receive a torque vector from the rate controller module; determine a rotational speed of the one or more motors to generate a desired flight orientation based upon the torque vector; and consider sensor data from the one or more sensors to adjust the rotational speed of the one or more motors.

An assistance system and method for assisting with the restart of at least one engine of an aircraft includes determining that at least one engine of the aircraft has flamed out and controlling an automated descent of the aircraft down to a predefined target altitude below which the altitude of the aircraft is conducive to at least one attempt to restart the at least one stopped engine.

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 method for controlling an aircraft capable of hovering is described, comprising a first engine; a second engine; at least one rotor; and a transmission interposed between the first and second engine and the rotor; the transmission comprises a first and a second inlet connected respectively to a first outlet member of the first engine and to a second outlet member of the second engine; the method comprises step i) of placing the in a first configuration, in which the first and second engine make available a first and a second power value; or in a second configuration, in which the first engine makes available a third power value greater than the first power value to the first inlet, and the second engine delivers a nil power value to the second inlet; the method also comprises, characterised in that it comprises the steps of ii) detecting a series of parameters associated with the operating conditions of the aircraft; and iii) enabling the transition of the aircraft from the first configuration to the second configuration, when the parameters assume respective first values.

An unmanned aerial vehicle includes a plurality of rotors, a plurality of electric motors each configured to drive a respective one of the plurality of rotors, a power source, and a controller configured or programmed to control supply of first electric power from the power source to the plurality of electric motors and supply of second electric power from the power source to an external implement, and control operation of the plurality of electric motors. Upon detecting an abnormality in equipment included in the unmanned aerial vehicle, the controller is configured or programmed to stop the supply of the second electric power to the implement and maintain the supply of the first electric power to the plurality of electric motors to execute flight using the plurality of rotors.

An unmanned aerial vehicle includes a plurality of electric motors each configured to rotate a respective one of a plurality of rotors, a plurality of motor drive circuits each configured to drive a respective one of the plurality of electric motors, and a controller configured or programmed to control operation of the plurality of motor drive circuits. The controller is configured or programmed to change the operation of the plurality of motor drive circuits from a flight state of the unmanned aerial vehicle to a state where flight is not possible in response to a stop signal.