The present application relates to a control method of an aerial vehicle. The aerial vehicle may comprise a propulsion structure for providing flight power and a spraying apparatus for spraying a material. The control method may comprise determining current target information of the aerial vehicle during a process of the aerial vehicle performing a spraying task, wherein the current target information indicates wind field strength of a downward pressure wind field generated by the propulsion structure; determining, based on the current target information, a desired relative flight altitude of the aerial vehicle corresponding to the current target information relative to the material being sprayed below the aerial vehicle; and controlling the aerial vehicle to fly toward the desired relative flight altitude.

An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The tail is removably coupled to the fuselage. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor.

A system and method for protecting a rotorcraft from entering a vortex ring state, the method including monitoring a vertical speed of a rotorcraft, comparing the vertical speed to a vertical speed safety threshold, and performing vortex ring state (VRS) avoidance in response to the vertical speed exceeding the vertical speed safety threshold. The performing the VRS avoidance includes determining a power margin available from one or more engines of the rotorcraft, limiting the vertical speed of the rotorcraft in response to the power margin exceeding a threshold, and increasing a forward airspeed of the rotorcraft in response to the power margin not exceeding the threshold.

When any one of a plurality of first rotors (VTOL rotors) fails, a rotor controller (a VTOL rotor controller) executes thrust increase control for increasing the thrust generated by an adjacent first rotor that is the first rotor adjacent to the failed first rotor, without making the adjacent first rotor cause the thrust variation for vibration suppression control, and executes the vibration suppression control in a manner so that one or more second rotors (VTOL rotors) bear the burden of the thrust variation that has been borne by the adjacent first rotor.

A system for controlling weight distribution of a remotely piloted aircraft is described. The system comprises a payload weighing platform, a control unit, and a counterweight gantry system. The payload weighing platform is configured to be positioned within the aircraft and receive the payload. The control unit is configured to: receive payload sensor data from the payload weighing platform; determine payload weight and payload center of mass; determine a target position for each of at least one counterweight, the target position determined to control a center of gravity of the aircraft by controlling the weight distribution of the aircraft; and provide a counterweight position signal to the counterweight gantry system. The counterweight gantry system is attached to the aircraft and is configured to move each of the at least one counterweight to corresponding target position in response to receiving the counterweight position signal.

A landing method, etc., for a flight vehicle having directional characteristics, which can improve the landing performance of the flight vehicle having directional characteristics by turning the airframe in a nose direction with a good balance between lift and drag based on wind speed data and wind direction data related to the landing site. In the method for landing a flight vehicle of the present invention, the flight vehicle comprises to generate lift in response to wind from the nose direction of the airframe and based on wind speed data and wind direction data related to the landing site, the nose direction of the airframe is controlled and the descent of the airframe is initiated.

A method for controlling an economy operating mode for an aircraft comprising two heat engines, only one of the heat engines being active and supplying mechanical power to the rotor in the economy operating mode. Operating parameters of the aircraft are measured and then compared with functional and safety limitations relating to the economy operating mode. When the aircraft is in the economy operating mode, if a functional limitation is not being respected by one of the parameters, an alert indicating the proximity of the functional limitations is issued in order to inform the pilot, and, if one of the safety limitations is not being respected, the economy operating mode is disengaged, each heat engine not supplying mechanical power to the at least one rotor being started.

A system and method for protecting a rotorcraft from entering a vortex ring state, the method including monitoring a vertical speed of a rotorcraft, comparing the vertical speed to a vertical speed safety threshold, and performing vortex ring state (VRS) avoidance in response to the vertical speed exceeding the vertical speed safety threshold. The performing the VRS avoidance includes determining a power margin available from one or more engines of the rotorcraft, limiting the vertical speed of the rotorcraft in response to the power margin exceeding a threshold, and increasing a forward airspeed of the rotorcraft in response to the power margin not exceeding the threshold.

A vehicle control framework enables improved attitude tracking and mode switching of a vehicle by modeling the vehicle as a switched system, where the vehicle is operable for changing a geometric configuration during flight. The vehicle control framework implements a control law that accommodates modeling uncertainties and unknown external disturbances. The vehicle also enforces a switching time constrained by a minimum dwell time which can be adaptively updated based on attitude errors.

An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The tail is removably coupled to the fuselage. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor.