A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

An aircraft is disclosed. The aircraft includes a first pair of wings, each wing in the first pair of wings including one or more actuating flaps configured to move to facilitate the aircraft transitioning between a forward cruise mode and a vertical hover mode, and operating in one of the forward cruise mode or the vertical hover mode. The aircraft further includes a second pair of wings, and one or more propellers coupled to the second pair of wings and oriented horizontally to provide upward lift.

A tail sitter aircraft includes a wing with a closed front section and a fuselage, from which the wing extends. The wing includes a first portion projecting from the fuselage and a second portion spaced from the first portion. The aircraft includes first and second connecting section that are interposed between the first and second portions. The fuselage extends parallel to a first axis and the first and second portions extend parallel to a second axis orthogonal to the first axis. The first axis is arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position.

This invention is a type of flying disc. It has very special features that makes it unique and an innovation. To the flying disc part one can add a handle, thus, making it a flying disc with a handle protruding downwards from the center of the flying disc part. To this flying disc with a handle, one can add many features like: an overhang, a dome, lights, sound devices, solar panels, computer, buttons, light sensors, speakers, TV screen, meteorological instruments, remote control, drone capabilities, flaps, wings, propellers, etc. Also, this flying disc with a handle rotates like a top on various surfaces. Thus, it is a flying disc and a top in one. To the flying disc with a handle, one can add or take off parts, like extensions, handle, and flying disc parts to create bigger or more interesting flying discs, as shown in the drawings.

This invention is a type of flying disc. It has very special features that makes it unique and an innovation. To the flying disc part one can add a handle, thus, making it a flying disc with a handle protruding downwards from the center of the flying disc part. To this flying disc with a handle, one can add many features like: an overhang, a dome, lights, sound devices, solar panels, computer, buttons, light sensors, speakers, TV screen, meteorological instruments, remote control, drone capabilities, flaps, wings, propellers, etc. Also, this flying disc with a handle rotates like a top on various surfaces. Thus, it is a flying disc and a top in one. To the flying disc with a handle, one can add or take off parts, like extensions, handle, and flying disc parts to create bigger or more interesting flying discs, as shown in the drawings.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.