Abstract: An induction lift flying saucer having a circular shaped air frame which houses a vacuum cell induction lift wing adapted to be used in an aerodynamic generating channel wherein the lift wing includes an airfoil having a leading edge and a trailing edge, a top panel and an acoustically treated hollow interior, and wherein the airfoil includes airtight partitions forming individual cells within the hollow interior and the airfoil has inclined slots extending from the top panel into each of the individual cells wherein the inclined slots extend at an angle from each of the individual cells toward the trailing edge of the airfoil and wherein the airfoil is adapted to be positioned within an aerodynamic generating channel with the top panel of the airfoil being adapted to form a lower boundary of the aerodynamic generating channel and to define a slip thereacross from an airstream passing through the aerodynamic generating channel, a bearing support operatively coupled to the airfoil adjacent the trailing edge to

Abstract: An aircraft comprising an aerodynamic annulus and a fuselage coupled to the annulus by electromagnetic means to permit rotation of the annulus relative to the fuselage without mechanical engagement upon a "frictionless" bearing. Jets mounted on the annulus rotate the annulus to produce a gyroscopic precession. One or more jets or driven propeller units mounted on the fuselage drive the craft in a selected direction. Direction of the fuselage, and hence the aircraft, may be provided by computer control of the fuselage jets or jets or by means of a rudder. Pivotal jets mounted on the annulus and/or fuselage together with retractable flaps on the annulus provide lift for vertical take-off and hovering.

Abstract: The invention relates to circular aircraft and in particular to circular aircraft having an impeller for providing horizontal and vertical thrust. Internal frameworks are provided for defining an outer circumference of convexo-convex shape, an impeller housing, a control, passenger and cargo section and an appendage bracket. Controls are provided on the aircraft for directional control and control of counter-rotation. Electrical power sources are provided to drive the impeller, as well as an alternate power supply in the form of an internal combustion engine.

Abstract: A flying object for collecting solar rays comprises a disk-shaped flying body equipped with floating and propelling means installed at the outer circumferential portions thereof. The flying object can detect its direction of flight and keep its position constant by means of the plural floating and propelling means. In addition, the flying object has a solar ray collecting device, equipped with solar ray collecting lenses. The solar rays collected by the solar ray collecting device are guided through an optical conductor cable into the flying object.

Abstract: A hovering or VTOL aircraft with a propulsion unit using a fan in a shroud whose upper end is toroidally shaped and rotationally symmetrical with a convex curvature with a radius of curvature between 0.2 r.sub.f and 1 r.sub.f from a location 1.4 r.sub.f upstream of the blade plane to a location 0.2 r.sub.f downstream thereof. The blade, whose tip radius is r.sub.f has a twist at least from a range of .+-.0.25 r.sub.f around a mean radius between hub and tip to the tip such that the airflow velocity through the meridian increases outwardly from the hub of the fan toward the periphery of the fan.

Abstract: A flying platform, propelled by at least one ducted fan causing a vertically downwardly directed airstream in and through a cylindrical duct. A vane system in the duct has two mutually perpendicular pairs of diametrically opposite first vanes, each extending in from the duct rim toward the center of the duct. Each pair of first vanes provides a pair of generally vertical walls parallel to a diametral line across the duct, and they define duct passages between the pairs of vanes and define quadrants between adjacent pairs. Each first vane has an upper, fixed, rigid portion and a variable camber flap depending therefrom. A first servomotor with linkages vary the camber of each pair of flaps, so that the camber of the flaps of each pair is at all times the same amount but in opposite directions. Preferably, there are also four second vanes, one bisecting each quadrant, and a symmetric pair of spoilers is mounted on each second vane.

Abstract: A flying disc aircraft includes a symmetrical body housing pilot and/or passenger seating apparatus above, a thrust-generating apparatus below, and a rotation inertia disc located therebetween. The disc rotates within the body in a plane normal to the axis of symmetry, and provides inertial stability for the aircraft through a gyroscopic effect. Directional control is achieved by means of mechanical linkage elements connecting a control stick at the pilot seating apparatus with the thrust-generating apparatus, the linkage allowing the pilot to orient the thrust at various angles relative to the aircraft axis of symmetry. Lift occurs when ambient air is induced, by virtue of the thrust-generating apparatus, to flow over the disc. In an alternate embodiment, lift is generated by the thrust-generating apparatus, and a shroud located beneath the apparatus is employed for redirecting resulting thrust to therefore facilitate directional control of the aircraft.

Abstract: A high-speed vertical take-off and land (HSVTOL) aircraft comprises a disk-shaped body with a annular rotor having a rotatable fan assembly driven by redirected jet exhaust gases. The rotatable fan assembly includes fan blades, each with movable airfoil portions, and stationary flap portions with nozzles located on the trailing edges. Low pressure inflatable O-ring seals and bearings are positioned along a labyrinth interface between the disk-shaped body and the rotor. The rotatable fan assembly of the rotor is connected to an annular plenum receiving the hot exhaust gases. For vertical flight, substantially all of the hot exhaust gases of the turbojet engines are redirected into the plenum by main bypass and control bypass doors. Converging ducts located in the rotor just upstream of the rotatable fan assembly receive and direct the hot exhaust gases from the plenum to radially extending feed tubes connected to the nozzles.

Abstract: An air vehicle for lifting loads generates lift forces from helium gas within a torus-shaped envelope having a central passageway, and from a fan arrangement designed to direct air downwardly through the passageway. Lateral propulsion units are provided on the envelope. In one embodiment, the fan arrangement comprises two fans carried by a saddle supported on the envelope, while in another embodiment a single fan is carried by a gondola suspended from the envelope.

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 hybrid annular airship of the kind including an annulus containing at least one gas containing portion is disclosed which is characterized by improved maneuverability, stability and speed. This improvement is effected by combined means comprising a pair of tubes mounted diametrically within the annulus and normal one to the other. A plurality of doors are provided for selectively closing off one or the other of the pair of tubes. Each tube is provided with a propulsion unit, having an access port, and preferably reversibly mounted therein. The tubes either are mounted on the same level or at different levels. Preferably, the propulsion units are jet engines which are individually operable. An elevator and a walkway preferably are provided communicating with each of the access ports leading to the propulsion units. Preferably, each access port has its own opening and closing mechanism.

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: A vertical take-off and landing (VTOL) aircraft is disclosed. In one embodiment designed for manned flight, the aircraft employs an aerodynamically-shaped body carrying a pair of lifting elements disposed longitudinally along the body on opposite sides thereof. The lifting elements extend outwardly and curve smoothly downward from a horizontal to a vertical orientation at the outboard edge. Lifting air is flowed over them transverse to the direction of flight. In a second embodiment designed for unmanned use such as cropdusting, military surveillance, or the like, the body is a single circular lifting element of parabolic cross-section. In both embodiments, a turbine is carried within the body to provide forward thrust and, primarily, a supply of pressurized air which is flowed through a nozzle slit opening outwardly over the tops of the lifting element(s) in confined segments.

Abstract: A model having a flying saucer shaped body which is provided with lift by means of a thrust producing device such as a reciprocating Wankel or turbine engine and a propeller. The body is prevented from rotating by means of counterrotational fins, and stability in the horizontal plane is provided by means of an internal gyro rotor actuated by the airflow from the propeller.

Abstract: A wingless aircraft that has a generally truncated cone fuselage that has a cockpit in the upper thereof in which the pilot sits, and a transparent rigid dome mounted on the upper portion of the fuselage that extends over the pilot. A number of equally spaced, elongate, jet engine assemblies are pivotally and adjustably supported within the fuselage, with each engine in communication with an air inlet defined in the fuselage. Each jet engine assembly includes a combustion chamber that has an elongate tubular nozzle extending downwardly therefrom, in which exhaust openings are defined through which the hot gaseous products of combustion discharge. The exhaust openings are elongate and substantially angularly disposed relative to the vertical, and as a result the exhaust gases not only rotate the nozzle but exert a reactive force sufficient to lift the fuselage to an airborne position.

Abstract: A spherical vehicle for operation in a fluid medium utilizes an actuator disk or propeller of approximately half the diameter of the sphere for propulsion. In addition to providing the energy for driving the sphere, the actuator disk acts to draw the flow of fluid smoothly over the after part of the sphere, thus avoiding or minimizing the tendency of the flow to separate from the surface of the sphere and create turbulence. For aircraft launch, a heavy shroud protects the actuator disk propeller and assures that the vehicle will sink rapidly after impact. The shroud is jettisoned at a desired depth. Steering in pitch and yaw planes is effected through the use of a plurality of powered thrusters located at or just behind the circle of maximum diameter (with respect to the direction of motion) and selectively actuated by a guidance or control system. Alternatively a single reversible thruster may be used for steering in yaw combined with a movable internal weight for pitch control.

Abstract: An aircraft containing aerodynamic and gyroscopic stability that has a high angle of take-off and landing capabilities, with high speed horizontal powered flight, but is also able to sustain power-off flight with auto-rotation of its multiple extending airfoils. The fuselage has the shape of an inverted saucer with aerodynamic configuration and has an open circular track at its periphery; and riding in this track is a rotary frame and extended airfoil assembly that isin-line with the fuselage. Each extending airfoil contains solid weighted bodies at their tips and this rotary frame and extended airfoil assembly is rotated on the track by an internal power unit. The extending airfoils taper toward their tips and these tips have a knife sharp edge for penetrating the air resistance.

Abstract: A flying craft has a supporting element with an opening in it. A driving unit with a propeller drives air downwardly through the opening. Vanes mounted on the driving unit break up the circular component of the air velocity and also counteract the torque on the driving unit. The downwardly moving air is formed into a laminar air stream by a second set of vanes which are connected to the supporting element for rotation therewith. The pitch of the vanes can be adjusted. Adjustment of the pitch of the second set of vanes may cause the supporting element to rotate and give the craft a gyroscopic stability. The craft is tiltable for maneuvering purposes.

Abstract: A rotationally symmetrical supporting member provides lift in response to movement of air over its upper surface, and such air movement is produced by the impeller of a coaxially arranged drive unit, the base of which is connected to the supporting member so that counter torque from the drive unit imparts rotational movement to the supporting member. A carrier which may hold a load or supporting steering flaps is rotatably mounted in relation to the supporting member and to the driving unit.

Abstract: An aerial device in the form of a disc which can be "sailed" in the air by throwing it in a manner to impart rotation to the disc. Vanes, holes and/or conduits are provided in the disc to force air from the top side or perimeter or other location to the underside thereof. By such means, increased lift is imparted to the device. Also, air cavities are provided to collect and maintain the air on the underside to provide an air cushion, further enhancing the lift imparted to the device.

Abstract: A lighter-than-air saucer or disc-shaped non-rigid airship is disclosed. A saucer-shaped flexible envelope is provided within which an annular pressurized tube is positioned so as to maintain the flexible envelope in a saucer shape when inflated. Walls within the envelope from a central chamber and a plurality of outer chambers symmetrically disposed around the central chamber. Typically a load such as a gondola is suspended beneath the central chamber. To maintain level horizontal flight stability, differential forces are developed by preferably providing the central chamber with heated air and the outer chambers with a lighter-than-air gas such as helium providing greater lift than the central chamber. Propulsion units are preferably arranged at opposite peripheral side edges of the envelope and maneuvering of the saucer-shaped airship is accomplished by rotating the airship.

Abstract: An aircraft is provided with a circular wing member which is rotatably mounted to a fuselage member. The circular wing member provides lift for horizontal flight and also provides gyroscopic stabilization of aircraft attitude. The circular wing member is substantially free of aerodynamically active flight control or propulsion members and, in a preferred embodiment, has a concentration of mass at its outer rim. The fuselage is provided with propulsion means for effecting and controlling vertical and horizontal flight. The propulsion means provides horizontal or vertical thrust along vectors which pass through the aircraft center of mass.

Abstract: An annular wing particularly suited for use in supporting in flight an aircraft characterized by the absence of directional stabilizing surfaces. The wing comprises a rigid annular body of a substantially uniformly symmetrical configuration characterized by an annular positive lifting surface and cord line coincident with the segment of a line radiating along the surface of an inverted truncated cone whereby a decalage is established for the leading and trailing semi-circular portions of the body, relative to instantaneous line of flight, and a dihedral for the laterally opposed semi-circular portions of the body, relative to the line of flight, the direction of flight and climb angle or glide slope angle being established by selectively positioning the center of gravity of the wing ahead of the aerodynamic center along the radius coincident with an axis for a selected line of flight.

Abstract: A rotationally symmetrical supporting member provides lift in response to movement of air over its upper surface, and such air movement is produced by the impeller of a coaxially arranged drive unit, the base of which is connected to the supporting member so that counter torque from the drive unit imparts rotational movement to the supporting member. A carrier which may hold a load or supporting steering flaps is rotatably mounted in relation to the supporting means and to the driving unit.

Abstract: An aircraft is disclosed which includes a body having the shape of an inverted cone with a downwardly extending rim formed about the edge thereof and a triangularly shaped tail section. The aircraft can be constructed as a glider or a powered device and several alternative tail sections are shown such as square, radii, circle and tangent.

Abstract: A flying disc capable of vertical takeoff, hovering, or powered horizontal flight. The disc includes a discoidal wing that is circular and includes a convex surface on an upper side and a concave lower surface. The wing also includes an inward leading edge that defines a circular opening centered on an upright central axis. The arcuate surfaces converge at the leading edge and at an outer concentric trailing edge. The discoidal wing is freely rotatable on a central support structure that also supports a cockpit. Two sets of turbine blades are affixed to the discoidal wing adjacent the leading edge. Thrust producing engines are mounted to the central support structure to direct thrust radially outward through the turbine blades. This results in rotation of the discoidal wing and produces lift. The angle of thrust may be adjusted such that the thrust is directed only across one or the other set of turbine blades or any selected variation between extreme positions to change the lift characteristics.

Abstract: An aircraft rotary wing aerofoil assembly comprising a generally planar annular frame supporting radially inner and outer sets of aerofoil blades, each set being disposed to form an annulus and supported on the frame for rotation about a common axis, and first and second sets of panels are mounted on the frame for movement to shroud portions of the inner and outer sets of aerofoil blades respectively.

Abstract: An aircraft comprising a generally annular wing structure surrounding a circular central structure to form an annular air duct, a pair of fuselages extending longitudinally at opposite sides of the aircraft, and rotor blades extending radially across the air duct from the central structure and rotatable relative to the central structure around the duct for inducing airflow through the duct to effect a lift on the aircraft. The annular wing structure consists of forward and rear wings forming air foils, the forward wing having a generally semicircular trailing edge and the rear wing having a generally semicircular leading edge.

Abstract: An annular, radial flow gas turbine engine and airborne vehicle utilizing same for jet propulsion. The engine comprises counter-rotating rotors and a compressor section with counter-rotating annular rows of intermeshing compressor blades, an annular combustion section common to both rotors wherein the combustion zone is defined by oppositely rotating rotor walls, and a turbine section made up of annular rows of counter-rotating exhaust turbine blades. No stator blades are present in either the compressor or the turbine sections.The craft comprises a central hub on which the engine rotors rotate on thrust bearings, and air bearings maintain rotor tolerances with respect to each other and to nonrotating shell portions above and below the engine rotors. Air inlet guide vanes leading to the compressor section are also housed in the hub portion of the craft.

Abstract: A fluid flow device comprises a rotor housed in a casing having slot-like intake and outlet openings. Groups of such devices can be used to form an aircraft propulsion system by drawing-in air from above through the intake openings and forcing the air downwardly through the outlet openings to provide lift and horizontal thrust, the effect being similar to that produced by the wing of a bird.

Abstract: A vertical lift device comprised of a generally vertically disposed cylindrical tunnel, open at the top and bottom ends, with a driven propeller axially mounted at the open top end to direct a stream of air downwardly through the tunnel. A first portion of the stream of air is spirally directed outwardly through a peripheral portion of the open bottom end to create first lift forces for the device by using jet stream action. A second portion of the air stream is directed downwardly through a central axially disposed tube in the cylindrical tunnel to twin fans which redirect the second portion upwardly into a truncated cone, surrounding the central tube, to increase the pressure against the inner wall surface of the cone to create second lift forces.

Abstract: A flying vehicle in the form of a fixed structure fitted with propulsion engines and in the form of a fixed wing and tail section mounted to a pair of counter-rotatable discs, one below and one above the fixed structure, with the discs when rotating providing both aerodynamic lift and gyroscopic stability.

Abstract: A method and apparatus to improve the performance of a Vertical Take Off and Landing (VTOL) aircraft having increased safety, efficiency and maneuverability is described. The utilization of an airbooster to achieve optimum air speed of jetted air, have made the increase in its efficiency feasible. A concealed rotor eliminates the great hazard of most VTOL.

Abstract: The aircraft in the nature of a helicopter is movable in a vertical direction when being raised from the ground or landing thereon. The body of the aircraft is toroidal in form, that is to say, the shape of a doughnut having a central aperture. The central aperture has a jet engine mounted therein providing a downward thrust on the centerline of the body aperture. A substantial ground effect is obtained by the use of panels which are movable from the underface of the body to a vertical position enclosing the central area therebeneath. Supports extend upwardly and outwardly from the central jet engine having a pivotally mounted turbine on each of the upper ends, the extending shafts from which have an elongated helicopter type of propeller mounted thereon. A ram, or other type of motor, is employed for tilting one or both of the turbines and propellers from an angular position to a position of greater tilt to provide a forward movement to the body.

Abstract: A flying ship is disclosed which comprises a hollow, saucer-shaped body having a convex upper surface surmounted at its center portion by a dome-shaped transparent canopy covering a passenger compartment, and a bottom including a generally concave major bottom portion, and an annular outer bottom portion which is inclined upwardly at its outer edge and is joined to the concave major bottom portion by a smooth upwardly open curve. Plural jet engines are adjustably mounted beneath the ship in a circular pattern inward of the outer edge and beneath the annular outer bottom portion to provide lift for take-off and landing, and horizontal thrust, as well as lift, for flight. An annular fluid motor is provided in the ship above the jet engines which includes an annular tube in which, an endless train of pistons is slidably mounted.

Abstract: A lighter-than-air craft having a discus shape. A passenger compartment is located at the top center of the craft and a payload pod at the bottom center beneath the passenger compartment. The pod connects to the passenger compartment by a passageway which extends up through the center of the craft. Moreover, the pod is detachable from the craft, and can be raised or lowered to the ground, thus eliminating the need to land the craft in picking up or discharging passengers and cargo. The discus shape, together with a plurality of automatically controllable ailerons distributed about the circumference of the craft, improve the stability and control of the craft in flight.

Abstract: A rotor arrangement for an aircraft comprising two coaxially counter-rotatable rotators, each rotor being journaled freely rotatable about an imaginary axis of rotation common to both rotors on or through a fuselage part or a support member, each fuselage part or support member being either rigidly connected to or journaled on the fuselage, each rotor together with the other respective rotor or with the component part of the support member or fuselage part supporting the first mentioned rotor constituting an integral part of an electromotor by forming the counteracting parts of the electromotor ("rotor" and "stator") which rotate relative to one another by securing a plurality of poles of the electromotor to the respective rotor and by arranging on the other counter-rotating rotor or on the component part of the support member or fuselage part supporting the first mentioned rotor the corresponding poles of the electromotor facing toward the poles of the respective rotor such that a reciprocal field effect exi

Abstract: An aircraft in which a concavo-convex disc carries a hub at its center. An engine carried by the hub provides vertical lift for the aircraft. The aircraft is stabilized by the rotation of the disc relative to the hub. This rotation is induced by a plurality of nozzles carried by disc through which a portion of the engine exhaust passes.

Abstract: An aerospacecraft possessing a discus shaped body equipped with at least one disc type air screw driven by a turbine by the exhaust gases of a jet engine. The disc type air screw is equipped with variable pitch blades and works in the manner of a helicopter rotor for the generation of lift.