Abstract: A free movement, lift mechanism employing a spinning disc utilizing Bernoulli's Theorem and the derivative Coanda and Couette effects augmented by centrifugal force. Lift control is provided by variation in rotational velocity of the disc, by variation in the width of a Couette space and by variation in the amount of air entering the Couette space. Strategically placed vanes provide stabilizing control.

Abstract: A system for producing vertical lift has a substantially rigid upper rotating disk (44) of dense solidity ratio whose discharge air flow is centrally routed via a vertical vortex shaft (24) to coact with lower coaxially rotating airfoil (34) and duct fan (36) elements. The upper disk (44) includes a spirally configured array of curved wings (40A-40D) which rotate in a first direction to produce lift and a cyclonic air discharge into an upper end of the vertical shaft (24). The lower rotating airfoil (34)/fan (36) elements are positioned at the lower end of the vertical shaft (24) and rotate in a counter direction to neutralize torques, induce downward air flow through the vertical shaft (24), and further provide lift and vertical thrust.

Abstract: An aircraft having an annular body, defining a central passageway; an upper deflector, a lower collector and a fluid drive in the passageway. Air is accelerated by the fluid drive and circulates around the annular body. The collector divides the circulating air and directs a portion into passageway and a portion to beneath the aircraft to provide a further thrust.

Abstract: A VTOL aircraft (100) is provided having a plurality of rotor blade sets (2) disposed at least partially beneath the fuselage (1). The aircraft is propelled vertically by means of the thrust generated from the rotating sets of rotor blades (2), and augmented by suction generated aerodynamic lift. At least a portion of the suction airflow (A) is displaced from the upper surface of fuselage (1), creating a region of low pressure. The negative pressure, or suction generated from the portion of the rotor blades (2) disposed beneath the fuselage (1) causes a column of air to be accelerated upwardly toward the central portion of the fuselage bottom surface (205). The upwardly directed airflow (R) contacts the fuselage bottom surface (205) and flows thereacross toward respective rotor blades (2), generating a layer of high pressure air in juxtaposition with the lower surface (205) of fuselage (1).

Abstract: The invention is a circular airplane with an oblately spheroidal body which derives lift from a wall or ribbon jet exhausting over its upper surface. The jet is produced by a mixed flow fan driven by an internal combustion or gas turbine engine within the body. A fixed guide van assembly removes the swirl from the outlet flow of the mixed flow fan. The jet exiting from the fixed guide vane assembly follows the curved surface of the body, exhausting downward, and produces lift. The magnitude of lift produced in each quadrant of the airplane may be reduced for thrust vectoring by flow control gates which partially block the flow of air from the fixed guide vane assembly. Rotation control vanes introduce a controlled swirl into the flow of air from the fixed guide vane assembly to effect rotation of the airplane. Actuators for flow control gates and rotation control vanes, and a flight control system, are provided.

Abstract: A thrust-producing device comprises a body having a surface and a periphery and disposed in a first fluid; a generator for imparting energy to a second fluid; and a distributor connected to the generator, disposed adjacent the surface, for distributing the second fluid in a first stream over and adjacent the surface for blanketing and enclosing at least a portion of the surface with the first stream and causing the first stream to be initially sufficiently unattached to the surface to define a closed volume between the surface and the first stream.

Abstract: Disclosed is a lift generating appartus for an aircraft which includes a generally circular principal wing with its peripheral portion bent downward, forming a bowl-shaped space opening downward; a high-pressure gas producing device provided on the principal wing; a plurality of jet nozzles provided within the central portion of the bowl-shaped space in a circular arrangement at angular intervals to jet a high-pressure gas produced by the high-pressure gas producing device radially outward from the central portion of the bowl-shaped space; and suction openings for sucking the external air as a secondary fluid from outside the bowl-shaped space by suction generated by the ejector effect of the high-pressure gas jetted from the jet nozzles. The supply of the secondary fluid into the bowl-shaped space in addition to the high-pressure gas further increases the static pressure within the bowl-shaped space, so that the lift acting on the principal wing is enhanced.

Abstract: An aircraft comprising a discoidal fuselage having a planar upper surface and containing at least one vertical duct extending longitudinally therethrough, an impeller located within the duct for producing an upward flow of gas, and a gas flow director movably mounted with respect to said duct. The vertical duct is central to the fuselage. The impeller is a vertical turbojet engine. The gas director comprises a central conical member, an upper annular flow control member, and a plurality of radially spaced apart vent controls. The vent controls are hydraulic cylinders. A hatch is mounted about the bottom opening of said duct. The hatch is movable such that one position seals the duct from the entry of liquids. An air passageway extends into and communicates with the duct.

Abstract: A novel and improved heavier-than-air flying craft (20) is the subject matter of this patent application. The craft (20) includes an airfoil (22), over an upper wall (28) of which multiple fluid streams are directed. The craft (20) can include a multiplicity of main engines (54) for directing the fluid streams. Vertical ascent and horizontal translational flight can be controlled by modulating the flow of exhaust from these engines (54). The craft (20) can further include auxiliary engines (58) for facilitating horizontal translational flight and yaw control engines (56) to augment yawing of the craft (20). None of the engines (54, 56, 58) have moving parts, and the airfoil (22) has no moving parts in the external air stream.

Abstract: An aircraft is provided with a wing in the form of an annulus having an airfoil shape in radial section, the wing being concentrically mounted on a vertical axle shaft which in turn is rotatably carried by a mounting on the fuselage. Rotation of the wing drives air centrifugally across the upper and lower surfaces to energize the boundary layer, enhance laminar flow, and produce lift. Vanes may be mounted on the inner portion of the surface to increase the flow and thus produce greater life. The vanes may be attached to a stabilizer ring which is eccentrically adjustable by a controlling mechanism to vary the extension of the vanes into and out of the wing at various points in the cource of rotation and thus vary the degree of lift produced. The wing may also be provided within its inner perimeter with airfoil lifting blades which produce additional lift, and the blades may be swung by a stabilizer ring to positions producing a desired thrust in a desired direction as the wing rotates.

Abstract: A land, water or air vehicle has a jet air stream unit mounted in front with a plurality of distributed jets generated immediately preceding the front wall portion of the vehicle to reduce the opposing pressure as well as the mass of air with the resulting greater ease in movement of the vehicle. As applied to an automobile type vehicle, an air pump is located immediately behind the radiator so as not to unduly interfere with the air flow through the conventional radiator. A small air jet forming unit is mounted in front of the vehicle having an inlet connected to the air pump and outlets directed at right angles to the line of motion. The jets are generally in a semi-circular pattern with the lower portion free of jets for removal of the air from immediately preceding the automobile while permitting sufficient air flow to the radiator.