An aircraft capable of Vertical Take-Off and Landing (VTOL) and traverse flight. The aircraft generally includes a fixed outer structure including at least a generally cylindrical wing having an internal body situated within the fixed outer structure. A space is defined between the internal body and the fixed outer structure. Within this space are one or more rotatable ring impellers that create(s) thrust sufficient to achieve lift for the aircraft.

An unmanned aerial vehicle (UAV) that provides increased operational flight endurance and efficiency. The UAV includes a power generation system, which includes an internal combustion engine and one or more batteries (batteries). The power generation system is configured to generate power for propulsion of the UAV. The internal combustion engine is configured to power a lift propeller, generating vertical lift of the UAV, and the batteries are configured to power a micro-propeller assembly, propelling the UAV in a forward direction or multiple additional directions.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

A vertical take-off and landing (VTOL) aircraft, that may be incorporated into a personal automobile, comprises a rectangular wing including an upper wing section having a right upper wing side and a left upper wing side, a lower wing section having a right lower wing side and left lower wing side, a right vertical wing section coupled to the right upper wing side and to the right lower wing side, and a left vertical wing section coupled to the left upper wing side and to the left lower wing side, the upper wing section having an upper wing cross section with a first asymmetrical airfoil shape configured to cause lift when in forward flight, the lower wing section having a lower wing cross section with a second asymmetrical airfoil shape for causing lift when in forward flight, each of the right vertical wing section and the left vertical wing section having a vertical wing cross section with a symmetrical shape to cause lateral stability when in forward flight; two elevons on at least one of the upper wing section and the lower wing section; at least one rudder on each of the right vertical wing section and the left vertical wing section; a support frame coupled to the rectangular wing; and a propulsion system coupled to the support frame.

A vertical take-off and landing (VTOL) aircraft has a first drivable configuration in which the pilot seat is positioned between the wings and facing the direction of forward travel. The VTOL may be driven in the first configuration as a normal automobile. In the first configuration the wings are aligned with the direction of forward travel and their surfaces are vertically oriented. In the first configuration, the VTOL may also attain altitude and be maneuvered using thrust from propulsion sources. In a second configuration, the pilot seat is rotated 90 degrees from the direction of forward travel to a direction of forward flight. Forward flight is achieved using thrust to rotate the wings from the vertical orientation to a lift-providing orientation. In concert with the rotation of the wings, the pi lot seat is counter-rotated to maintain the seat facing the direction of forward flight.

Apparatus for vertical or short takeoff and landing, and operational control during flight. In one embodiment, the apparatus includes a main body assembly, the main body assembly including: a fuselage, the fuselage includes one or more power motor assemblies and one or more actuator motor assemblies; a plurality of power mounting bodies and a plurality of power/articulation mounting bodies; a static rail that is operatively coupled with the plurality of power mounting bodies; a transient rail that is operatively coupled with the plurality of power/articulation bodies; and a plurality of airfoils, each of the plurality of airfoils being coupled to a respective power/articulation mounting body. Various sub-systems of the apparatus and methods of manufacture and use are also disclosed.

Systems and methods to improve stability and control of an aerial vehicle are described. For an aerial vehicle having a ring wing around a fuselage and a plurality of propulsion mechanisms, one or more sections of the ring wing may be pivotable to reduce vibrations and forces transferred to the aerial vehicle, and to prevent stall and minimize turbulence experienced by the aerial vehicle. The pivotable sections of the ring wing may be freely pivotable, may include locking elements to prevent or allow pivoting, may include bias elements or dampening elements to partially control the free pivoting, or may include actuators to effect desired pivoting.

Various reconfigurations of wing sections of a ring wing of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, one or more wing sections may be modified to maintain control and safety of the aerial vehicle. In example embodiments, positions, angular orientations, and/or pitches of one or more wing sections may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing that provides lift whenever the aircraft is in forward flight, 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. One or more engines or motors are disposed within or attached to the closed wing, fuselage or spokes. Three or more propellers are proximate to a leading edge of the closed wing or the one or more spokes, distributed along the closed wing or the one or more spokes, and operably connected to the one or more engines or motors. The propellers provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.

An aircraft including a body, a first propeller assembly, a second propeller assembly, a flight control surface, and a parachute. The first propeller assembly is coupled to the body and configured to provide vertical lift. The second propeller assembly is coupled to the body and configured to provide horizontal thrust. The flight control surface is operably coupled to the body. The parachute extends from the body and is arranged to facilitate aircraft takeoff.