An unmanned aerial vehicle and a landing method for unmanned aerial vehicle are provided. The unmanned aerial vehicle includes a positioning device and a processor. When the processor detects a fight status of the unmanned aerial vehicle, the processor obtains a current coordinate from the positioning device. According to the current coordinate, a predetermined route, and a plurality of emergency landing coordinates, the processor calculates a plurality of distances for the unmanned aerial vehicle moving from the current coordinate to each of the emergency landing coordinates along the predetermined route. According to a shortest distance among the plurality of distances, the processor obtains a target emergency landing coordinate. The processor controls the unmanned aerial vehicle to move to the target emergency landing coordinate along the predetermined route.

A method for automatically powering off an aerial vehicle includes determining an operating state of the aerial vehicle, and in response to a determination result that the operating state of the aerial vehicle is a landed state, triggering to shut down a propulsion output of the aerial vehicle such that the aerial vehicle completes automatic power off after landing, including, in response to the determination result that the operating state of the aerial vehicle is the landed state, determining whether the propulsion output of the aerial vehicle is currently enabled and determining whether an automatic take-off operation indicated by an automatic take-off instruction is currently being performed, and, in response to the propulsion output being currently enabled and the automatic take-off operation not currently being performed, triggering to shut down the propulsion output of the aerial vehicle.

A method for automatically powering off an aerial vehicle includes determining an operating state of the aerial vehicle, and in response to a determination result that the operating state of the aerial vehicle is a landed state, triggering to shut down a propulsion output of the aerial vehicle such that the aerial vehicle completes automatic power off after landing, including, in response to the determination result that the operating state of the aerial vehicle is the landed state, determining whether the propulsion output of the aerial vehicle is currently enabled and determining whether an automatic take-off operation indicated by an automatic take-off instruction is currently being performed, and, in response to the propulsion output being currently enabled and the automatic take-off operation not currently being performed, triggering to shut down the propulsion output of the aerial vehicle.

A method for automatically powering off an aerial vehicle includes determining an operating state of the aerial vehicle, and in response to a determination result that the operating state of the aerial vehicle is a landed state, triggering to shut down a propulsion output of the aerial vehicle such that the aerial vehicle completes automatic power off after landing, including, in response to the determination result that the operating state of the aerial vehicle is the landed state, determining whether the propulsion output of the aerial vehicle is currently enabled and determining whether an automatic take-off operation indicated by an automatic take-off instruction is currently being performed, and, in response to the propulsion output being currently enabled and the automatic take-off operation not currently being performed, triggering to shut down the propulsion output of the aerial vehicle.

A method for automatically powering off an aerial vehicle includes detecting an operating state of the aerial vehicle based on altitude information of the aerial vehicle. The attitude information includes at least one of absolute altitude information or relative altitude information. The relative altitude information includes a landing distance to a landing plane. The method further includes determining whether the operating state of the aerial vehicle indicates that the aerial vehicle has landed and, in response to a determination result that the aerial vehicle has landed, shutting down a propulsion output of the aerial vehicle.

An apparatus is provided for causing an unmanned aerial vehicle (UAV) to perform a contingency landing procedure. The apparatus includes memory and processing circuitry configured to cause the apparatus to at least determine candidate safe landing zones (SLZs) within an estimated current range of the UAV. Trajectories are generated for landing the UAV in respective ones of the candidate SLZs. Risk values are calculated that quantify third-party risk associated with operation of the UAV along respective ones of the trajectories to the respective ones of the candidate SLZs. A flight termination risk value is calculated that quantifies third-party risk associated with immediately landing the UAV at the current position. The lowest of the risk values is compared with the flight termination risk value, and a sequence is executed to operate the UAV along the trajectory to the selected one of the candidate SLZs, or immediately land the UAV.

Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.

Rotorcraft including a fuselage and at least three rotor system arms each having a rotor system. Each rotor system includes a mast having at least two rotor blades and an electric rotor motor. At least one rotor system arm includes a support mechanism for pivotally supporting a floating mast about at least one pivot axis whereby the floating mast is tillable relative to a fiducial tilt position. The floating mast has a controllable cyclic rotor blade pitch. A mast tilt measurement mechanism provides a mast tilt feedback signal regarding a measured tilt position of a floating mast relative to its fiducial tilt position. A flight control system continuously controls the at least three electric rotor motors and the floating masts cyclic rotor blade pitch in response to a desired input maneuver and its mast tilt feedback signal.

Methods, apparatus, systems and a vertical take-off and landing (VTOL) vehicle are provided. The VTOL vehicle includes: a fuselage having longitudinally a front section, a central section and a rear section; a first lifting surface comprising two wings respectively secured to opposite sides of the rear section of the fuselage; a second lifting surface comprising two wings respectively secured to opposite sides of the front section of the fuselage; where each wing comprises at least one engine module, each of the engine modules being pivotally coupled to the wing and each engine module being independently controlled for transitioning between a vertical mode of flight and a horizontal mode of flight.

A flight control method of an agricultural unmanned aerial vehicle (UAV) includes controlling a rotation device to rotate continuously to drive a radar detection device to rotate continuously, obtaining detection information at a plurality of rotation directions during continuous rotation of the radar detection device, and controlling take-off and landing of the agricultural UAV according to the detection information.