Example embodiment provides an aircraft with improved agility. The aircraft includes a main body, at least two wing assemblies, at least two motors, and a controller. The wing assemblies are attached to the main body. Each motor tilts one wing assembly with a tilting angle. The controller is connected with the motors for controlling the tilting angle of the wing assembly. Each wing assembly further includes a wing, a power plant, and a propeller that is driven by the power plant for providing propulsion. Each wing assembly tilts with an individual tilting angle, so that the aircraft can fly with improved agility. The power plants and propellers on the wings can each be controlled independently in synchronism with the tilting wings.

An aircraft has a propulsion unit and a fuselage unit. The propulsion unit has a first rotor for providing a propulsion force on the aircraft. The fuselage unit extends along a rotation axis of the first rotor and has a rotationally symmetrical shape with respect to the rotation axis of the first rotor. The fuselage unit has a suspension at a first end by which the fuselage unit is coupled to the first rotor so that the fuselage unit is spaced apart from the first rotor along the rotation axis. A detection unit for the detection of environmental information is provided in the area of a second end of the fuselage unit. The propulsion unit is designed to keep the aircraft in a hovering flight condition so that a relative position of the aircraft with respect to a reference point on the Earth's surface remains unchanged.

An unmanned aerial vehicle (UAV) includes a radar configured to perform ranging on a ground during rotation and a terrain prediction device communicatively connected to the radar. The terrain prediction device includes a memory storing a computer program and a processor configured to execute the computer program to acquire N pieces of ranging data each being obtained by the radar when a rotation angle of the radar is within a preset angle interval, and determining a terrain parameter of the ground according to the N pieces of ranging data. N is an integer greater than 1. The terrain parameter includes at least one of a gradient or a flatness.

A method of trajectory control for a vehicle includes obtaining an initial trajectory; presenting the initial trajectory as a current trajectory on an I/O device, the current trajectory presented overlaying terrain; initiating travel of the vehicle along the current trajectory; updating the current trajectory and the terrain in real time as the vehicle travels along the current trajectory; determining if change in the current trajectory is required; changing the current trajectory to an altered trajectory in response to determining change in the current trajectory is required; and presenting the altered trajectory on the I/O device, the altered trajectory presented overlaying the terrain.

A rotary wing driving apparatus includes a motor, a rotary wing, and an electromagnetic brake. The rotary wing is attached to a shaft of the motor. The electromagnetic brake is attached to the shaft of the motor.

This unmanned aerial vehicle has: a main body; a plurality of rotary wings provided on the main body; a wire for suspending an object from the main body; a hook attached to the wire; a winch for rotatably supporting a spool on which the wire is wound in the forward and backward directions, winding the wire by rotating the spool in the forward direction and unwinding the wire by rotating the spool in the backward direction; and a controller for restricting the backward rotation of the spool when the tension of the wire becomes less than a first threshold value, and restricting the forward rotation of the spool when the tension of the wire becomes less than the first threshold value and becomes equal to or less than a second threshold value, which is less than a gravitational force acting on the hook.

[Object] To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. [Solution] The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.

A rotor wing aircraft provided with a propulsion apparatus is disclosed. The aircraft has a rotating mast configured to rotate said rotor wing and the apparatus includes a pole mechanically connectable to the rotating mast of the aircraft. At one of the ends of the pole there is placed an electric turbine, powered by a battery, and configured to rotate the pole around an axis of the rotating mast in such a way that the rotation of the pole can be used to rotate the rotor wing. Preferably the pole is made of carbon fiber.

A network is provided for recharging aerial drones during extended flight operations, without requiring a return to a centralized recharging station. Instead, autonomous recharging stations are provided which are self-sustained by using electricity from renewable energy sources located at the station. Operationally, a cone-shaped receptacle is mounted on the drone, and a cone-shaped probe is provided at the recharging station. The probe is connected with the renewable energy source. With this connection, an engagement for recharging the drone's battery is accomplished when the vertex of the probe is received through the open base of the receptacle to place an electrical connector on the probe in contact with the battery of the drone.

One embodiment of a vertical take-off and landing aircraft held aloft by way of one or more powered assemblies of wing type elements capable of generating aerodynamic lift by means of rotation. A main body having an integrated means for directing air impelled from an inlet, by way of one or more powered impellers, through a cavity, acting as a duct, to an outlet. At least one movable surface located in sufficient proximity to the outlet to direct expelled air in a vectored manner providing a means of affecting the motion of the aircraft.