A ducted fan device integrated with a permanent magnet synchronous disc flat wire motor for a flying copter car, including a rotor system, a stator system, an air intake/exhaust control system, a detection system, a driving system and a power supply system. The stator system includes a motor shell, and flat wire coils respectively arranged on an upper end face and a lower end face of an inner wall of the motor shell are connected in series. The rotor system is arranged inside the stator system, including axial flow and radial flow composite integrated blades and permanent magnets. A part of centrifugal blades are replaced by the permanent magnets which are located on an outer side.

An air mobility vehicle may include air flaps located under a mounting position of each of rotary wings and rotatably mounted inside openings to guide a flow direction of air flowing to a region under each of the rotary wings or air flowing above the openings to inside of the air mobility vehicle, an actuator coupled to the air flaps and configured to rotate the air flaps to direct the air having passed through the air flaps to a motor, an inverter, or the motor and the inverter of each of the rotary wings, or batteries, and a controller electrically connected to the actuator and configured to control a flow of the air having passed through the air flaps by controlling the actuator depending on a driving state of the air mobility vehicle or temperatures of the motor and the inverter of each of the rotary wings or a temperature of the batteries.

A foldable propeller for air mobility includes a link assembly including a plurality of links facilitating blades to be rotated around a hub as a moving portion vertically slides such that the blades are folded to each other or unfolded from each other.

A ducted fan of an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan radially at the outside and defines a flow channel for air flowing via the fan. The stator-side duct has an inner wall that faces toward the rotor-side fan and which is perforated at least in certain sections. The stator-side duct has an outer wall that faces away from the fan. Between the inner wall and the outer wall of the stator-side duct, there are formed cavities which, forming sound-deadening resonators, are coupled via the perforated inner wall to the flow channel for the air flowing via the rotor-side fan. The cavities are filled, in a region which faces away from the inner wall and thus faces toward the outer wall, with activated carbon.

An aircraft includes a fuselage that provides an aircraft passenger cell and a plastically deformable protective body secured on the fuselage. The plastically deformable protective body can be secured on the bottom of the fuselage and/or laterally on the fuselage. The plastically deformable protective body can be secured releasably on the fuselage, for example, via a screw connection.

Various embodiments of systems, apparatus, and/or methods are described for enhanced responsiveness in responding to an emergency situation using unmanned aerial vehicles (drones). Drones are fully autonomous in that they are operated without human intervention from a pilot, an operator, or other personnel. The disclosed drone utilizes movable access doors to provide the capability of vertically takeoff and landing. The drone also includes an emergency recovery system including a mechanism to deploy a parachute in an event of a failure of the on-board autopilot. Also disclosed herein is a drone port that provides an IR-based docking mechanism for precision landing of the drone, with a very low margin of error. Additionally, the drone port includes pads that provide automatic charge to the drone's batteries by contact-based charging via the drone's landing gear legs.

A winged vertical take-off and landing aircraft with compound control surfaces comprising flaps and ailerons which can be operated simultaneously with each other offers improved aerodynamic performance and maneuverability. Configuration of the compound control surfaces may be varied to optimize performance in hovering (vertical) flight modes, cruising (horizontal) flight modes, and transitional flight modes.

An exemplary integrated battery cargo platform includes a housing having an exterior surface and a structural strength to support cargo for transit on a top surface, a battery enclosed in the housing with power contacts exposed at the exterior surface.

A vertical take-off and landing aircraft using a hybrid electric propulsion system, according to an embodiment of the present invention, includes: a first control step (S1) of changing a destination when an engine (10), a power generator (20), an engine control unit (30), a power management device (40), a control unit (50), a battery management system (60), a main battery (62) and the like malfunction, thereby causing a normal flight to be difficult; a second control step (S2) of performing control so that an aerial vehicle (1) glides to a point (T), at which same has entered a first space (CEP-1) required for landing or a wider second space (CEP-2) considered safe, and maintains lift and has minimized flight air resistance after passing through the point (T); a third control step (S3) of performing control so that lift is increased and performing control so that a nose cone is switched into an upward direction; and a fourth control step (S4) of performing control so that lift is gradually reduced, and controlling a second variable-pitch control device (122) so that thrust does not act on the aerial vehicle at the moment the aerial vehicle lands, and thus the present invention can vertically land while minimizing impact to be applied to the aerial vehicle.

A motor-integrated fan having an intake port and a blow-out port comprises a rotary part 12 that is rotatably supported by a shaft, and a motor 14 that rotates the rotary part 12. The motor 14 is an outer periphery drive motor that rotates the rotary part 12 by supplying motive power from a duct provided on the outer peripheral side of the shaft. The motor 14 includes: a permanent magnet 45 provided on a rotary support ring 33 connected to the outer peripheral side of blades 32 of the rotary part 12; and a coil 46 provided opposite the permanent magnet 45 in the axial direction of the axis of rotation. Among the plurality of blades 32, a first blade 32a and a second blade 32b are located at different positions in the axial direction.