Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports and rear exhaust ports. The air-craft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.

An unmanned aerial vehicle is disclosed. The unmanned aerial vehicle includes a frame configured to fix a motor. The unmanned aerial vehicle also includes a housing configured to enclose the frame. The housing includes a top mesh corresponding to an upper surface of the housing and a bottom mesh that covers a portion of a bottom surface of the housing. The housing also includes middle part coupled to the top mesh and the bottom mesh. The housing also includes a plurality of duct areas that penetrate each of the top mesh, the bottom mesh, and the middle part. The motor and a propeller connected to the motor and for rotating are positioned within the duct area.

A double-ring rotary wing spherical cabin aircraft includes a spherical cabin; an upper protective cover; a lower protective cover; a rotary wing fixing ring connected between inner circles of the upper and lower protective covers, and mounted with a gyroscope and a rotatable attitude-adjusting ring; an upper rotary wing rotor and a lower rotary wing rotor rotationally mounted on the rotary wing fixing ring; and a control system. The spherical cabin is rotationally mounted in the attitude-adjusting ring. Two attitude-adjusting articulated shafts opposite to each other are connected between the attitude-adjusting ring and the rotary wing fixing ring. Two cabin articulated shafts opposite to each other are connected between the spherical cabin and the attitude-adjusting ring. The attitude-adjusting articulated shaft and the cabin articulated shaft are in transmission connection with an attitude-adjusting motor. The attitude-adjusting motor and the gyroscope are electrically connected to the control system.

A compact lift generating system is provided. The lift generating system embodies a wind tunnel enclosure extending between an inlet and an outlet. An airflow generator may be fluidly coupled to the enclosure inlet, an intake of a feedback conduit may be fluidly associated with the enclosure outlet, and an airfoil disposed therebetween. Airflow is urged to engage the airfoil, producing lift. The airflow generator may include a fan, an amplifier and an air knife fluidly coupled in series, wherein an output end of the feedback conduit fluidly connects between the airflow generator and the amplifier. A plurality of wind tunnels enclosures may be operatively associated in series. A plurality of airfoils may be provided in a stacked orientation in one wind tunnel enclosure.

The invention relates to an aircraft with vertical takeoff and landing and its operation method. Aircraft with vertical takeoff and landing of aerodyne type according to the invention comprises a circular symmetrical aerodynamic body (1) having an internal stiffening platform (2) located on the chord of the aerodynamic profile and which supports the components of the aircraft, at least four vertical ducted propellers (3a), (3b), (3c), (3d) arranged symmetrically to the central vertical axis of the carrier body (1), but also to the predetermined flight axis and to the transverse axis of the carrier body (1), propellers (3a) and (3c) having the same rotational direction opposite to that of propellers (3b) and (3d) at least two horizontal ducted propellers (4) with opposite rotation directions located inside the carrier body or outside of it, placed parallel symmetrical with the predetermined flight axis and on both sides of it, vector nozzles (5), one for each horizontal propeller (4), which provides vector orientation to jets of the horizontal ducted propellers (4), the means of power supply (6), which are designed to provide electricity necessary to operate all engines and all electrical and electronic devices on board, an electronic control and management flight module (7) and a landing gear (9), which aims to promote contact between the aircraft and the ground.

A vertical takeoff and landing aircraft has a circular body with a cockpit at the center, and multiple vertical, horizontal, and other directional through tunnels inside the body. A propelling device such as ducted fan, jet turbine or rocket is provided inside each tunnel. Each propelling device is completely disposed within a tunnel with no exposed parts. The bottom surface of the aircraft has a circular lip forming the lowest part of the aircraft, and the portion of the bottom surface surrounded by the circular lip is concave, where the multiple vertical through tunnels open to the concave portion. A control system controls the thrust produced by each propelling device so as to precisely control the horizontal and vertical speed and the pitch, roll, and yaw angles of the aircraft. Communication and positioning equipment are provided onboard, as well as various sensors. The aircraft may be manned or unmanned.

An inertial force polarizer apparatus including a rotor frame member comprising a plurality of rotor nests, a plurality of rotor assemblies rotatably mounted to the rotor frame member, each rotor assembly includes a shaftless rotor having one or more attachment members, and a motor having a rotatable shaft coupled to the one or more attachment members, the motor configured to drive rotation of the shaftless rotor about an axis, wherein a rotation of the shaftless rotor generates an inertia on the rotor frame member.

A coleopter may have maximum lift up to tens of thousands of tons and is an optimum lift device of a disk aircraft. However, an existing coleopter may provide thrust consistent with an axial direction of the coleopter only, but cannot provide thrust perpendicular to the axial direction. Therefore, like other existing disk aircrafts, a wing ring flying saucer must be additionally provided with an aero-engine capable of specially providing thrust in a horizontal direction, otherwise cannot fly fast, while due to the extra engine, effective carrying capacity is inevitably seriously compressed, and energy consumption, pollution and noise may be increased. In the present invention, the flying saucer may be driven to fly fast without the extra engine, and can turn, brake and fly backwards. The method is as follows: fins of the wing ring or fluid generators are enabled to repeat the same deflection process while passing by a specific section in circular motions of two times or more than three times in succession, so that a force perpendicular to the axial direction is formed from an original resultant force consistent with the axial direction of the wing ring (that is, a resultant force formed by lift produced by all the fins), thereby enabling the wing ring flying saucer to fly, turn and go backwards at high speed.

An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

An apparatus configured with two subsystems comprising a torus tube, linear flow, and turboplant assemblies that form of cavity for externally supplied and rotating subsonic working fluid. The working fluid rotation is provided by turboplant assemblies with throttle control. The rotating working fluid inside the cavities will conserve angular momentum. As a result of the conservation of angular momentum, poinsot flow fields are seen within the working fluid. A stable, resultant force is generated from the pressure and area forces inside the cavity. The apparatus usage is either with manual operation or as an unmanned, autonomous vehicle.