A radio controlled (RC) vehicle includes a receiver configured to receive a radio frequency (RF) signal from a remote control device. The RF signal indicates command data in accordance with a first coordinate system that is from a perspective of the remote control device. The command data includes a lift command associated with a hovering state of the RC vehicle. One or more motion sensors are configured to generate motion data that indicates a position of the RC vehicle and an orientation of the RC vehicle. A processor is configured to transform the command data into control data based on the motion data and in accordance with a second coordinate system that is from a perspective of the RC vehicle. A plurality of control devices are configured to control motion of the RC vehicle based on the control data.

An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.

A method of controlling an unmanned aerial vehicle executing a mission in a defined mission area including a first observation area within a Visual Line of Sight (VLOS) of a First Observer (FO), a second observation area within a VLOS of a second observer (SO), and a transition area within the VLOS of both the FO and the SO, the method including: the vehicle moving into the transition area after completing part of the mission within the first observation area, in sight of the FO; and in response to the vehicle moving into the transition area, determining whether the vehicle is in sight of the SO. The vehicle is including multiple processing systems in wireless communication with multiple remote user interfaces and a radar sensor mounted on the vehicle using a moveable mount for moving the radar sensor between different radar orientations, the radar sensor generating a range signal.

A locking device for an aircraft is described, comprising a body adapted to be fixed to a support surface, a first ring and a second ring rotatable the one with respect to the other with respect to a rotation axis between a first angular position and a second angular position. The first and second ring enclose an area for the landing of the aircraft and are contained within the body. The locking device also comprises a plurality of cables, which connect the first ring to the second ring. The locking device is positionable in an unlocking position, wherein the first and second ring are in the first angular position, the cables are spaced from said area; or in a locking position, wherein the first and second ring are in the second angular position and the cables occupy a region of the area, so as to cooperate in contact with the aircraft to constrain it with respect to the support surface.

A locking device for an aircraft is described, comprising a body adapted to be fixed to a support surface, a first ring and a second ring rotatable the one with respect to the other with respect to a rotation axis between a first angular position and a second angular position. The first and second ring enclose an area for the landing of the aircraft and are contained within the body. The locking device also comprises a plurality of cables, which connect the first ring to the second ring. The locking device is positionable in an unlocking position, wherein the first and second ring are in the first angular position, the cables are spaced from said area; or in a locking position, wherein the first and second ring are in the second angular position and the cables occupy a region of the area, so as to cooperate in contact with the aircraft to constrain it with respect to the support surface.

The embodiments of the present invention disclose a rotor driving system, wherein at least three first actuators can drive a nonrotating lower-rotor swashplate to tilt towards a specific direction by cooperating with each other such that a rotating lower-rotor swashplate, lower tilted-arm pull rods and blade-clamp tilted arms of the lower rotor are all in motion, thereby driving first blade clamping bodies to be twisted relative to a lower rotor hub; at least three second actuators can drive a nonrotating upper-rotor swashplate towards a specific direction by cooperating with each other such that a rotating upper-rotor swashplate, upper-rotor steering rodL arms, lower upper-rotor steering rods, pull rods, upper upper-rotor steering rods, upper tilted-arm pull rods, blade-clamp tilted arms 42 of the upper rotor are all in motion, thereby driving a second blade clamping body to be twisted relative to an upper rotor hub. Thus, in the solution, the structure of a rotor driving system is simplified, thus solving the problems of a low production efficiency of the process and of inconvenient testing and maintenance.

A mounting device for mounting electronic components of an unmanned helicopter. A solid base plate has a circumferential outer edge. A connecting module is fixedly attached to the circumferential outer edge. The connecting module is configured to reversibly connect a flexible cover to the base plate.

A method for providing medical services to a patient, including: receiving a medical service request associated with a patient location; selecting an aircraft, located at an initial location, from a plurality of aircraft based on the patient location and the initial location; determining a flight plan for flying the aircraft to a region containing the patient location; at a sensor of the aircraft, sampling a first set of flight data; at a processor of the aircraft, autonomously controlling the aircraft to fly based on the flight plan and the set of flight data; selecting a landing location within the region; and landing the aircraft at the landing location, including: sampling a set of landing location data; determining a safety status of the landing location based on the set of landing location data; outputting a landing warning observable at the landing location; at the sensor, sampling a second set of flight data; and in response to determining the safety status and outputting the landing warning, autonomously controlling the aircraft to land at the landing location based on the second set of flight data.

A method for optically acquiring a wind turbine for monitoring purposes with the aid of an aircraft, in particular a manned or unmanned rotorcraft, which has at least one camera installed thereon, wherein the wind turbine comprises a plurality of rotor blades, the surface of which is scanned within the scope of the method.

Method and apparatus for planning and modifying a vehicle operation plan. A vehicle operation plan for a vehicle schedule is determined based on performance constraints of the vehicle and an operational rule file that defines operational restrictions on the vehicle based on states of the vehicle. In the event a state changes from a planned state, the vehicle automatically and autonomously recalculates the vehicle operation plan in a manner that satisfies the performance constraints and the operational restrictions.