An air mobility device improves propulsion due to the Coandă effect when flying so as to increase a flying range and reduces noise when flying.

An aircraft landing assist apparatus includes an image obtaining unit, a shape obtaining unit, a measuring unit, and a calculating unit. The image obtaining unit is configured to obtain an image of a surrounding region of a landing point on which an aircraft is to land. The shape obtaining unit is configured to obtain a shape of the surrounding region of the landing point on the basis of the obtained image. The measuring unit is configured to measure an above-air wind direction and an above-air wind velocity. The calculating unit is configured to calculate a landing-point wind direction and a landing-point wind velocity on the basis of the obtained shape of the surrounding region of the landing point, the measured above-air wind direction, and the measured above-air wind velocity.

In an aspect of the present disclosure is a system for in-flight re-routing of an electric aircraft including a battery pack configured to provide electrical power to the electric aircraft; a sensor configured to detect at least a temperature metric of the battery pack and generate a temperature datum based on the at least a temperature metric; a controller communicatively connected to the sensor, the controller configured to: receive the temperature datum from the sensor; and re-route the electric aircraft based on the temperature datum.

A proximity detection system for facilitating charging of electric aircraft. The proximity detection system includes at least a computing device. The at least a computing device is configured to receive a detection datum from at least a sensor, determine a proximal element as a function of the detection datum, and communicate a notification as a function of the proximal element to at least one of the electric aircraft and a charging structure. The detection datum includes information on at least one of the electric aircraft and the charging structure. The proximal element includes information on a spacing between the electric aircraft and the charging structure. A proximity detection method for facilitating charging of an electric aircraft is also provided.

A ducted-rotor aircraft includes a fuselage, first and second ducts, and a spindle that is coupled to the fuselage. Each duct includes a rotor having a plurality of blades. The first and second ducts are coupled to opposed ends of the spindle. The spindle is rotatably coupled to the fuselage with first and second bearings. The first bearing is configured to react to radial loads and the second bearing is configured to react to both radial and axial loads. The spindle includes a shaft, first and second fittings secured to opposed ends of the shaft, and first and second attachment interfaces that are attachable to the first and second ducts. The attachment interfaces may be integral with the fittings. Alternatively, the fittings may be configured to be secured to the attachment interfaces with fasteners.

An aircraft for vectoring a plurality of propulsors includes a longitudinal component attached to a fuselage, a plurality of downward directed propulsors attached to a plurality of laterally extending elements secured to the fuselage, a sensor attached to the plurality of downward directed propulsors, a flight controller, wherein the flight controller is configured to receive a flight datum as a function of the sensor, and vector the plurality of downward directed propulsors along a boom axis as a function of the flight datum.

An electric vertical take-off and landing (eVTOL) vehicle is positioned to be in a charging position on the ground, wherein the eVTOL vehicle is capable of performing vertical take-offs and landings. The battery is charged while in the charging position on the ground using a wind turbine that includes the rotor.

The present invention relates to the propulsion system and aircraft with vertical take-off and landing—VTOL that uses aerodynamic phenomena of thrust amplification, including at zero speed, to reduce the thrust/weight ratio. According to the invention, an individual aircraft 1, with vertical take-off and landing, uses a fuselage 2 in the form of a frame 3 that merges two propulsion system, 4 and 5 one in the front and the other in the rear, of the bi-planar type, located at the ends of the fuselage 2. The propulsion system 4 uses two wings 6 and 7, which are superimposed, parallel and distanced by a certain distance D. The rear wing 7 is fixed perpendicularly to the frame 3 in its median area, so that an angle α between 25° and 80° is formed with the horizontal plane in static position. The front wing 6 and the rear wing 7 are secured at their ends by two jet limiters 8. Similarly the rear propulsion system 5 uses two wings 8 and 10. On each rear wing 7 and 10 are installed a number of electric motors 11, preferably located at equal distances from each other. Each electric motor 11 actuates a tractor propeller 12.

An aircraft includes an airframe with a thrust array attached thereto. The thrust array includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A landing gear assembly is coupled to the airframe and includes a plurality of landing feet. An altitude sensor array includes a plurality of altitude sensors each of which is disposed within one of the landing feet such that when the aircraft is in the VTOL orientation, the altitude sensor array is configured to obtain multifocal altitude data relative to a landing surface. The flight control system is configured to generate a three-dimensional terrain map of the surface based upon the multifocal altitude data.

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.