Embodiments of the present disclosure provide a blade-stator system and the vertical take-off and landing flight apparatus comprising the blade-stator system, the blade-stator system including a duct disposed inside a flight body, upper and lower sides of the duct being open, and an inside of the duct being hollow; a blade assembly installed rotatably inside the duct and including a blade body of which an angle is changeable; a stator assembly connected to the blade assembly and the duct, supporting the blade assembly, and rotatable by a predetermined angle; a controller electrically connected to the blade assembly and the stator assembly and configured to control driving of the blade body and the stator assembly, wherein the angle of the stator assembly is changed in response to receiving an electrical signal from the controller so as to be interlocked with a change of the angle of the blade body.

Disclosed herein are a method for manufacturing a propulsion unit having a rim foil, which can significantly reduce drag during forward flight while protecting a rotor blade from surrounding obstacles, a propulsion unit manufactured by the same, and a flying vehicle including the propulsion unit. The method includes: a plate member formation step in which an airfoil-type plate member is formed to have an outline forming an airfoil shape in side view; a rim foil formation step in which a through-hole is formed in the airfoil type plate member to form a rim foil member having an outline forming at least a portion of an airfoil shape in side view; and a rotor blade installation step in which a rotor blade is installed in the through-hole.

A multirotor aircraft with an airframe that extends in a longitudinal direction, and with at least one thrust producing unit for producing thrust in a predetermined thrust direction, wherein the at least one thrust producing unit comprises a shrouding that is associated with at least one rotor assembly comprising at least one electrical engine, wherein the shrouding defines a cylindrical air duct that is axially delimited by an air inlet region and an air outlet region, wherein a cantilever is mounted at a leading edge region of the cylindrical air duct to the shrouding such that the cantilever is arranged inside of the cylindrical air duct and oriented at least essentially in parallel to the longitudinal direction, wherein the shrouding comprises a forward beam which connects the cantilever to the airframe, the forward beam being arranged outside of the cylindrical air duct and comprising a forward flange that is rigidly attached to the airframe, wherein the at least one electrical engine is mounted to the cantilever, and wherein the cylindrical air duct is provided in opened perimeter configuration, the shrouding being at least partly cut-off in the opened perimeter configuration at a trailing edge region of the cylindrical air duct over a predetermined opening angle.

An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor creates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

A transportation system and method serve passenger-conveying VTOL air vehicles (AVs) at a vertiport. The vertiport has a flight deck including at least one landing pad, a passenger terminal, and a dynamic partition arrangement that defines a capsule for receiving one of the AVs at a time. The dynamic partition arrangement assumes a first open state in which it is open to the flight deck and closed to the passenger terminal and a second open state in which it is closed to the flight deck and open to the passenger terminal. A robotic system includes a handling robot that automatically approaches and docks with the AV after landing, and conveys the AV between the landing pad and the capsule via an opening provided by the first open state of the dynamic partition.

A transportation system and method serve passenger-conveying VTOL air vehicles (AVs) at a vertiport. The vertiport has a flight deck including at least one landing pad, a passenger terminal, and a dynamic partition arrangement that defines a capsule for receiving one of the AVs at a time. The dynamic partition arrangement assumes a first open state in which it is open to the flight deck and closed to the passenger terminal and a second open state in which it is closed to the flight deck and open to the passenger terminal. A robotic system includes a handling robot that automatically approaches and docks with the AV after landing, and conveys the AV between the landing pad and the capsule via an opening provided by the first open state of the dynamic partition.

Provided is an air cleaner that can take a large amount of air in a large space into a dust collector with good efficiency while being lightweight and having easy maintenance. An air cleaner is provided with a drone and a dust collector. The drone has a main body unit and propellers attached to the tips of frames. The dust collector has electric discharge electrodes and a dust collection electrode. The electric discharge electrodes are connected to a booster unit within a central chamber. The booster unit is electrically connected to a control unit in the main body unit. Electric discharge is formed between the dust collection electrode and the electric discharge electrodes, and dust particles in the air are charged and collected by the dust collection electrode.

Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation.

The invention is for a VTOL (vertical take-off and landing) rotorcraft with the annular contra-rotating rotary wings and auxiliary propulsor. The rotary wing of the annular contra-rotating rotary wings is driven by a plurality of tangential forces applied at multiple locations of the inner hub or at the tip of the blade. The annular contra-rotating rotary wings can be shrouded with a nacelle for the improvement of propulsive efficiency, reduction of noise and protection of the rotary wing. The fuselage is mounted along the center axis of the rotary to be outside of the thrust slipstream. The auxiliary propulsor includes a quad independent pusher propeller to propel the rotorcraft to reach faster forward speed.