Abstract: Vertical lift in an aircraft is produced by driving a column of air downwardly, through an annular thrust-flow channel which is formed in the body (fuselage) of the aircraft. The aircraft also has an aerodynamic shape which is capable of developing lift responsive to forward flight. The annular thrust-flow channel is provided with a flow control mechanism which is capable of directing the developed air flow in varying orientations between a substantially vertical (axial) orientation for developing stationary, vertical lift (i.e., hovering) and a vectored (angled) orientation for developing a vertical component for producing lift and a horizontal component for producing forward (or rearward) flight, or flight to either side.

Abstract: A triple mode aircraft which can take off as a helicopter, or in gyrocopter mode with no power to the rotors or as a conventional aircraft obtaining lift from a circular wing and in another embodiment from short stub wings; a canard wing and high lift tailplane. So it combines the flexibility of a helicopter with the same efficiency and safety of a gyrocopter and a fixed wing aircraft, also has the same simplicity and efficiency of flying a helicopter that doesn't have a tail rotor to worry about. The rotor craft includes two counter-rotating rotors with weighted tips on one set of rotors or a circular airfoil (CA) attached to at least one set of rotors. This CA gives the lift to function as a conventional aircraft, it also weights the tips of the rotor to give a gyro-stabilizing effect to the whole aircraft. Also there is a down draft rudder that functions as a rudder in horizontal flight or catches the down draft from the rotors for directional control.

Abstract: A lift apparatus using the method of blowing air over the upper surface of the apparatus to generate lift by virtue of the balance of outside pressures against the body of the apparatus. It does this by using the expansion characteristic of supersonic gas stream in a divergent space to create low pressure above the upper surface and to maintain the attachment of the stream to the surface. For power source, it uses the hybrid internal combustion engine of a co-pending invention in its jet operation mode to jet the air. And it solves the working substance supply problem by recycling.

Abstract: In accordance with the present invention, there is provided an aerodynamic control device for integrated use with an aircraft having an inboard lifting member. The inboard lifting member having a leading edge, a pair of opposing distal edges and a trailing edge. The control device is provided with a movable outboard member which extends substantially about the leading, distal and trailing edges of the inboard lifting member and is spaced apart therefrom. The outboard member is provided with a leading edge portion, a pair of opposing distal edge portions, and a trailing edge portion which are collectively movable in unison in relation to the inboard lifting member to form an uninterrupted airfoil surface extending about the inboard lifting member and the outboard member for achieving desired aerodynamic control of the aircraft.

Abstract: A lift rotor assembly for a compound aircraft having a fuselage, including at least one circular disk structure with a plurality of bladelets spaced peripherally thereabout, a drive shaft coupled to a power source at a first end for rotating the drive shaft at low torque, a hub coupled to each circular disk structure and being located concentrically about the drive shaft, a gear drive coupled to a second end of the drive shaft opposite the first drive shaft end, and a first gear coupled to the gear drive and the hub for the circular disk structure located adjacent to the gear drive, wherein the first gear is operated at high torque to rotate one of the circular disk structures. The lift rotor assembly also includes a gear reduction apparatus associated with the gear drive in order to operate the first gear at high torque, as well as a constant velocity joint connecting an upper portion and a lower portion of the drive shaft.

Abstract: A remote-control flight vehicle structure includes an inner housing fixedly mounted, an outer housing rotatably mounted on the inner housing along a vertical axis thereof, an annular wing fixedly mounted on the outer periphery of the outer housing to rotate therewith and inclined with the horizontal plane about a first included angle, a plurality of baffles each fixedly mounted on the bottom portion of the annular wing along the radial direction thereof and each inclined with the annular wing about a second included angle, a platform fixedly mounted in the inner housing, a motor mounted on the platform, and a rotary axle including a first end portion rotatably mounted in the motor and a second end portion extending through the inner housing and fixed to the outer housing for rotating the outer housing.

Abstract: An aircraft for vertical take off and landing is comprised of a rotor assembly mounted on a rotating drive shaft extending from the top of a cabin. The rotor assembly is comprised of a truncated-cone top, a spaced apart circular bottom, and internal vanes running radially, between the top and bottom, forming an air impeller. In operation, air is drawn through the central air intake of the top and discharged through an annular nozzle around the circumference of the rotor assembly. As the top rotates, additional air is rammed through scoops mounted at an angle to radii of the top, on the surface of the top. The torque applied to the cabin, due to rotation by the engine of the rotor assembly, is countered by the reaction force generated by a plurality of tabs extending from the cabin sidewall into the airstream flowing downwardly from the nozzle.

Abstract: An aircraft utilizes a buoyant evacuated rotating envelope to provide at least a portion of the lift required. The rotating envelope may be in the form of a disk, cylinder or other suitable shape. In one embodiment, an evacuated rotating envelope in the form of a disk is utilized. The disk is provided with a central core tube with at least one jet engine mounted therein. The deflection of the exhaust causes rotation of the envelope. A non-rotating payload compartment is mounted to the rotating envelope by bearings. Structures are provided for deflecting the exhaust to be utilized for lateral propulsion as well as for stabilizing the payload compartment to prevent rotation. Two other embodiments utilize rotating cylinders which may be rotated either by a jet engine mounted within a core tube or by an off center jet engine which drives the cylinder.

Abstract: A body lift airplane assembly including 1) a main air lift body assembly of substantial length and width; 2) a landing gear/wheel assembly retractably connected to the main air lift body assembly; 3) a fixed wing assembly secured to and extended above the main air lift body assembly and having a fixed wing member of a length equal to the width of the main air lift body assembly; 4) an engine propulsion power assembly having a pair of spaced jet engine pod assemblies mounted within engine cut-out portions in outer edges of the main air lift body assembly; and 5) a fin and rudder assembly of a V-shape connected to a central rear portion of the main air lift body assembly. The main air lift body assembly includes a main body assembly having outer peripheral side and rear edges formed with downwardly extended arcuate air lift portions to provide air lift characteristics to the overall main air lift body assembly.

Abstract: A turbine airfoil unit is described which enables an aircraft to ascend and descend vertically. Multiple turbine airfoil units may be arranged within a large disk-like structure and thereby overcome size limitations placed on helicopters by their rotors. One or more central engines providing a flow of air under pressure relative to ambient air supplies power to one or multiple turbine airfoil units. The pressurized air from the engines is funneled into the containing disk-like structure and distributed to all turbine airfoil units encompassed therein. The supplied air acts on the turbines to rotate the airfoils and thus create lift. The lift is transmitted to the disk-like structure and to the remainder of the aircraft by bearings between the turbine airfoil unit and the containing portion of the disk-like structure. The large disk-like structure is known in the popular culture as a flying saucer.

Abstract: An aircraft with automated means to transport. Spherical or one of its segments, without airfoils for lift or guidance. Means for flight are housed within the aircraft. The outer-most sureface is configured to disrupt the air-flow, over its surfaces, in flight. This, to reduce skin-friction and drag coefficients, and mollify heat build-up on the skins outer surfaces as speeds increase to and beyond mach 1. The weight of gas per unit volume, with temperature variations, is the means to reduce the gross-weight and adjust for temperature and weight changes during flight. Propulsion, within the propulsion component, is provided by turbojet engines. They are secured within an inner compression pod and an outer combustion pod. The compression pod and the attached vertical-air-duct, rotate through three hundred sixty degrees, as the means for directional guidance and direct thrust. Augmented power-thrust-tubes extend outward from the combustion pod to the mid-horizontal circumference of the aircraft.

Abstract: A combined flying machine comprises a fuselage (1) in the form of a central hick wing with a vertical open tunnel (2), in which there is mounted a lifting rotor (4). Said machine is also provided with outboard wings and a tail unit (8). The machine is equipped with a landing device on an air cushion (19) that surrounds an outlet from the tunnel. A power plant of said flying machine comprises two engine modules (13), disposed from two sides of the tunnel (2) and connected with the lifting rotor (4) and the propulsion propellers (12). The area of the tunnel cross-section in the plane of the lifting rotor rotation amounts to 0.3 to 0.8 of the area of the landing device air cushion, which ensures a safe landing of the flying machine on an unprepared landing site even with a failure of one of the engine modules.

Abstract: A discus-shaped aircraft is provided with a peripheral jet arrangement for generating lift and, in the bottom of the aircraft, at least one rocket engine supplied with silicon hydride and compressed air and operated under conditions in which the silicon hydride is reacted with nitrogen of the compressed air to form silicon nitride while the nitrogen of the silicon hydride compounds reacts with oxygen to form H.sub.2 O.

Abstract: A flying craft (14) has a dish shaped body (18, 20, 21) with a convex upper surface (18) to provide lift. Engine means (1) in the form of a jet or rocket engine is housed in the body at the rear, while a duct (15) extends through the body from an air opening (15A) at the front of the craft (14) so as to direct air to the engine means (1) for example to serve as cooling and/or combustion air for the engine means. Additional thruster jets (16A, 16B) can be located on the bottom of the body for directional control. In a further embodiment (FIG. 12), an electric motor driven fan (37) is located in the duct (15) to form a ducted fan propulsion and unit for forward, slightly descending, movement of the craft (14A), while a more powerful jet or rocket engine (35) is located vertically in the craft to effect vertical ascent of the craft to an elevation where forward motion by the ducted fan propulsion unit can commence. A turbine fan driven alternator (27) can also be located in the ducting (15).

Abstract: A vehicular lift wing having a Coanda edge perimeter, is provided with a zle slot formation from which fluid ejection is directed tangentially from the full Coanda edge perimeter during translation through an ambient fluid medium. Omnidirectional control means supplies pressurized fluid to the nozzle slot formation at different azimuthal locations along the Coanda edge perimeter for selectively controlled generation of dynamic forces exerted on the wing.

Abstract: A ducted fan 20 provides lift to a flying vehicle 10. The ducted fan includes direction control vanes (1, 2, 3, 4) for controlling torques applied to the vehicle, and also includes lift negation vanes (305, 306, 307, 308), which control the available lift. The lift negation vanes are oriented with their longitudinal axes parallel to the forward-aft axis (9) of the vehicle in order to reduce drag at high forward velocities. The thrust negation vanes include fixed (305) and movable (305M) portions, with the movable portions rotatable so as to extend into the duct airflow to cause turbulence. The direction control vanes are airfoils arranged for rotation about their quarter-chord axes (410), which reduces the amount of torque required for rotation of the direction-control vanes. This, in turn, allows stepper motors (924a) to be used to drive the vanes. The effects of forward velocity on the ducted fan also creates effects which tend to pitch the vehicle nose-down.

Abstract: A body configuration for improving the fluid-dynamic performance efficiency of aircraft and watercraft comprises a generally conical upper segment (54) and a generally conical lower segment (56) that are joined at a common base plane (53), achieved by inverting the conical lower segment (56). The slopes of the conical surfaces are determined by the prescribed planform of the craft or vehicle and by the height of the conical segments wherein the height of the conical upper segment (h.sub.u) is less than and typically two-thirds that of the conical lower segment (h.sub.L). Although not limited to elliptical planforms, a generally circular planform (52) is preferred for a vertical takeoff and landing aircraft operating in the subsonic flight regime and an elliptical planform (68), with a large aspect ratio for takeoff and low-speed flight, then rotating to a low-aspect-ratio orientation for supersonic flight operation, is preferred for supersonic transport and single-stage-to-orbit type aircraft.

Abstract: A reusable space craft having a disk-shaped casing which receives buoyancy upon horizontal travel through a gas atmosphere and three drive systems on the casing. A first drive system utilizes counter-rotating rotors driven by jet engines on the periphery. A second drive system utilizes a rocket rotor which can swing out from the both of the casing into an inclined position. The third drive system is a main thruster rocket at the center of the bottom fueled by an Si.sub.5 to Si.sub.9 silane propellant.

Abstract: An air vehicle that includes a body lower portion, a body intermediate portion, body lower portion, a solar panel, elevating apparatus, gimbling apparatus, and inflatable landing gear. The body lower portion has a body lower portion outer surface and contains a body lower portion chamber. The body intermediate portion has a body intermediate portion upper surface and contains a body intermediate portion chamber. The body intermediate portion is connected to the body lower portion. The body upper portion contains a body upper portion chamber and is displaced a distance above the body intermediate portion. The solar panel has a solar panel outer surface and contains a solar panel void. The solar panel connects the body upper portion to the body intermediate portion. The elevating apparatus raises and lowers the air vehicle and is disposed within the body upper portion chamber.

Abstract: Apparatus and method for controlling an unmanned generally aerodynamically symmetric aircraft includes detecting the presence of misalignment between the horizontal component of the center of gravity vector and the horizontal component of the direction of flight vector and further includes rotating the aircraft to align the horizontal components of the vectors.

Abstract: An aircraft of disc-shaped configuration provides the capability of vertical take-off and landing; straight horizontal flight; and three-dimensional maneuverability in the air by means of a plurality of counter-rotating lifting rotors assembled of fixed pitch or of self-adjusting pitch aerofoil blade elements; and, submersibility of the aircraft in water is achieved by means of a marine propulsion module using two counter-rotating hydrofoil rotors for up or down thrust, and a tunneled conventional marine propeller for horizontal travel. The marine propulsion module is detachable for emergency and for use with the main frame aircraft of a variety of other detachable modules for different tasks and missions. Exceptionally adaptable for any existing power plant, including nuclear, it is best suited for the environment-friendly types, like integrated steam motor on hydrogen and oxygen burning.

Abstract: The present invention relates in general to aeronautical engineering and concerns specifically transport vehicles for transportation of liquid and loose cargoes. The invention provides an airborne vehicle capable of carrying a multiton cargo from a limited ground area. The object of the invention is accomplished due to the fact that in the airborne vehicle of the present invention the lifting aerodynamic airfoil system is made of two parts, that is, a stationary part in the form of a ring-shaped fuselage 1, consisting of aerodynamic members 2 and 3 curved spanwise, and a movable part in the form of lifting rotor units 6 arranged along the ring perimeter. A power unit of the vehicle comprises a gas-generator, propulsive units, ramjet ducts, and flywheel members interconnected through a reversible rotary-reciprocating engine-supercharger 22 and a fluid converter.

Abstract: A flying toy disc with a pivoted fuselage, the disc flying spinning in flight upon being thrust with a forward spinning motion, the disc having a particular transverse configuration which taken with the pivoted fuselage tends to stabilize the flight of the disc by having air streams co-act upon the lower and upper surface of the disc to stabilize the flight.

Abstract: A flying vehicle has wheels for highways, and a body and an engine. The body, engine and load define a center of mass (CG). Shrouded fans are located about the CG so as to produce, in conjunction with air jet redirection apparatus, the torques required to assume various attitudes. In one embodiment, an upper shrouded fan, with a diameter no greater than eight feet, produces an air jet, centered above the CG, for lifting the body. A second shrouded fan, smaller than the first, produces an air jet for lift, centered below the center of mass, on the longitudinal axis of the vehicle, forward of the CG. Third and fourth paired shrouded fans produce air jets for lift, centered below the CG, on either side of the longitudinal axis of the vehicle, toward the rear of the body. The paired second and third fans have equal diameters, no greater than half of the diameter of the upper fan, to keep the total width eight feet.

Abstract: A circular wing aircraft in the form of a helicopter comprising a fuselage and a circular wing assembly. A structure is for mounting the circular wing assembly above the fuselage in a stationary manner. An air impeller unit is rotatively carried within the circular wing assembly. A device is for driving the air impeller unit to rotate about a central axis within the circular wing assembly, so as to provide lift and flight movement while yaw control is maintained.

Abstract: A thrust unit for an aircraft having a lift unit for propelling the aircraft in upward flight. The lift unit includes a duct for directing air substantially downwardly, the duct being shaped so that air exhausting from its downstream end is in a stream having substantially the same cross-sectional dimension of the duct at the downstream end, and an air pump disposed for inducing a draught of air through the duct. In use, the draught of air exhausting from the duct can produce an upward thrust and is substantially non-convergent.

Abstract: One embodiment of a coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors includes a single stage transmission, a transmission housing, and a center hub support structure that are structurally and functionally interactive. The transmission housing includes upper and lower standpipe housings secured in combination with a middle housing. The single stage transmission includes an input pinion gear rotatably mounted in combination with the middle housing, and upper and lower spiral bevel gears rotatably coupled in combination with the input pinion gear to provide counter-rotation thereof. The spiral bevel gears include integral rotor shafts, respectively, rotatably mounted in the standpipe housings.

Abstract: A flying disc capable of vertical takeoff, hovering, or powered horizontal flight. The aircraft configuration comprises a circular disc-like airfoil-shaped wing structure having a convex upper surface and a concave lower surface with a leading edge and a trailing edge. At least one thrust-producing unit is attached at each of the leading and trailing edges, respectively. A plurality of other thrust-producing units are mounted symmetrically about the circular wing structure. Each thrust-producing unit has attached thereto a thrust deflector assembly for angularly adjusting the thrust produced by the thrust-producing unit, thereby allowing the aircraft to fly both vertically and horizontally. A substantial volume of helium gas is stored encompassing the inner upper hull of the aircraft, thereby giving the flying disc greater lift capacity. The outer skin of the upper surface consists essentially of a plurality of solar panels for delivering power to a multiplicity of devices.

Abstract: A vertical lift aircraft includes a central cabin and a set of concentric, circular, counter-rotating power blade assemblies. Gas turbine engines located in the central cabin provide power for rotating the power blade assemblies to cause lift and motion of the aircraft. The turbine engine exhaust gases are directed through a rotatable exhaust nozzle for aiding in the thrust and momentum of the aircraft. The gas turbine engines drive electric power generators which provide the necessary power for operation of the aircraft.

Abstract: A vertical lift aircraft comprising an aircraft body and a lifting assembly is presented. The lifting assembly comprises a frame wherein at least one airfoil assembly which includes a plurality of airfoils attached to a drive ring is secured. As the drive ring rotates, the airfoils move through the air and create lift. The pitch of the airfoils or blades can be fixed or variable. The drive ring is rotated by a band which is in frictional contact with the inner surface of the drive ring. The band is rotated by at least one pair of rollers which are in frictional contact with the band. Aircraft stability is controlled by regulating airfoil pitch which is responsive to pivoting of a control ring. Alternatively, aircraft stability is provided by regulating the flow of air or gas from a plurality of nozzles disposed about the aircraft. The body, a portion of which may be located inside the lifting assembly, includes a passenger and load carrying compartment and an engine assembly.

Abstract: The aircraft comprises a rotor with a vertical axis arranged in a housing for generating a lift exceeding the weight of the aircraft. The housing is essentially shaped as a circular wing. A first way of guiding air is provided for controlling the air stream generated by the rotor, by means of which the position of the aircraft can be controlled in hovering flight. From hovering flight, the aircraft can be moved into a cruise flight, where the lift of the aircraft is generated aerodynamically by the circular wing of the housing and its forward thrust by a propeller. For the transition between hovering flight and cruise flight, a second way of guiding air is provided for controlling the pitch of the aircraft. The structure for the second way of guiding air is arranged outside a zone defined by the air stream of the rotor.

Abstract: An aircraft having a generally circular or disc planform configuration provides the capability of vertical flight through two concentric sets of lifting fans or blades. The two sets may each include a number of individual rings of blades, but both sets are equal in area and rotate oppositely in order to provide nearly equal volumes of airflow, and thus essentially offset any torque reaction due to the rotation of the blade sets. Several engines are provided in the preferred embodiment, with one engine providing power to the lift fan sets and other engines providing thrust for horizontal flight. Other novel features are also disclosed, such as a peripheral aerodynamic control system, power transmission system, and surface vane system. An alternate embodiment includes a peripheral passenger or cargo area, with more conventional rearwardly located aerodynamic controls for horizontal flight.

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 present invention provides a vertical takeoff and landing aircraft vehicle in which a ducted fan with upwardly directed inlet discharges air generally horizontally across a segmented circular wing. Said wing segments are individually controllable in pitch and each includes a spoiler and split flaps to increase effectiveness and sensitivity in lifting and controlling the aircraft. Directional stability and thrust for horizontal movement is provided by controls directing different proportions of total airflow to the various segments around the aircraft and varying the direction of said airflow both radially and vertically. Power failure protection is provided by means for maintaining free rotation of the fan until needed to provide lift at touchdown.

Abstract: A rotary airscrew having a central hub with coaxial first and second counter-rotating drive shafts, a first set of a plurality of non-lift blades connected to the first drive shaft for rotation to be rotated for moving air therewith, a second set of a plurality of primary airfoil blades connected to the second drive shaft, to be rotated counter to the rotation direction of the plurality of non-lift blades, and spaced apart from the non-lift blades with a small clearance distance to allow non-contacting counter-rotation, and a ring for supporting the first and second sets of blades with a small clearance distance between the ends as they are rotated.

Abstract: A method and means for generating a force. A flared body is enclosed in a shroud to form one or more ducts of axially diminishing cross-section for accelerating and directing the discharge of a fluid introduced into the ducts under pressure. A cambered vane is positioned at the exit of each duct, in the path of the accelerated fluid discharge. Fluid passing over and under each vane produces a force aligned axially with the body and in the direction of flow of the fluid in the associated duct. In a preferred embodiment a conically-shaped body and surrounding shroud form an annular duct for air delivered to the mouth of the duct by a compressor. The vane is an annular airfoil.

Abstract: An unmanned aerial vehicle having a toroidal fuselage that surrounds a pair of coaxial, multi-bladed, counter-rotating rotors. The toroidal fuselage has an airfoil profile that is optimized to provide high hover efficiency and produce a pressure distribution that provide high lift forces. The airfoil profile is further optimized to counteract the undesirable nose-up pitching moments experienced by ducted rotary-type UAVs in forward translational flight.

Abstract: An aircraft having a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies within said body for effecting a vertical lifting air stream through said assemblies. Power generating devices and devices for coupling the power generating devices to the turbo-blade assemblies for maintaining them in rotary motion. It also includes thrusting devices coupled to the power generating devices for applying horizontal thrust to the aircraft, retro-boosting devices including a plurality of combustion chambers located below the turbo-blade assemblies for boosting said vertical lifting airstream.

Abstract: In a vertical take-off and landing craft, a pair of nested dome-shaped shells are spaced apart and rigidly interconnected by struts. The outer shell has a central opening formed in its top, and the shape of the shells is such that the space between the two shells progressively widens from the central top part of the shells to the peripheral bottom part of the shells. A circular series of arcuate airfoil units is disposed in the annular space between the bottoms of the shells, and is driven in rotation by an engine mounted on the inner shell. Upon rotation of the circular series of arcuate airfoil units, low pressure is generated above the airfoil units and high pressure below, such that air is drawn down through the central opening of the outer shell to produce a thrust which permits vertical displacement of the aircraft.

Abstract: An aerodynamic vehicle includes a central body with a vertical axis, an outer wall and a bottom wall, a first rotatable disk concentric with the central body axis and rotatable in a first direction, a second rotatable disk concentric with the central body axis and rotatable in a second direction opposing the first direction, first and second blade members respectively mounted in the first and second disks draw fluid radially inward and vertically downward to compress the fluid into a funnel-shaped fluid passageway. Selectively vectorable nozzle members are in communication with the passageway for discharging the compressed fluid below the central body to provide lift for the aerodynamic vehicle. Jet engines are mounted on the device for providing additional thrust and for generating hydraulic and electric power for the vechicle control system.

Abstract: The aircraft has a pair of rotors driven to counter-rotate within a housing. The housing has adjustable air guiding discuss for the rotor stream and a airfoil-like outer shape to generate lift at horizontal flight. The air guiding devices include a circular arrangement of a plurality of individual sectors having tangentially extending blades arranged in a zone below the rotors. In each sector the blades are adjustable in their position relative to the rotor stream. In at least some of the sectors, the blades are arranged in pairs for an adjusting movement in opposite relative sense. The air guiding devices allow precise and easy control of the aircraft maneuvers.

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 heavier-than-air craft having a cylindrical external configuration comprising a single annular airfoil forming a circumferential lift wing. This fixed circular wing is surrounded by a circular fuselage of substantially the same diameter, closely spaced axially above and below the outer periphery of the annular airfoil, to allow radial air flow over and under substantially the full circumference of the airfoil. The radial air flow is induced through an axial opening in the center of one surface of the circular fuselage by an engine driven propeller, fan or jet effect.

Abstract: An aircraft having a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies within said body for effecting a vertical lifting air stream through said assemblies. Power generating devices and devices for coupling the power generating devices to the turbo-blade assemblies for maintaining them in rotary motion. It also includes thrusting devices coupled to the power generating devices for applying horizontal thrust to the aircraft, retro-boosting devices including a plurality of combustion chambers located below the turbo-blade assemblies for boosting said vertical lifting airstream.

Abstract: In order to increase the lift supporting underpressure force on top of the inlet fairing of a shrouded fan of a lifting engine and in order to reduce the negative lift generating force of the inlet momentum acting on the rotor area of the fan, a particular geometry of the inlet fairing contour in connection with a particular twist of the fan rotor blades (3) is applied. This results in large differences of static pressures between front side and rear side of the fan at outer radii and there will be more small pressure difference at inner radii. This causes an apparent small change of the blade angle .beta. along a mean radial range of the rotor blades. Guide vanes ( 25) which might follow downstream of the fan rotor blades in some design cases, will have an arrangement of radial twist distribution mirror symmetrical to that of the rotor blades.

Abstract: Vertically starting and landing centrifugal toric ring shape, transport capsules for movement in any desired medium. The capsules consist of circular ring shells, arranged above or inside each other, and rotating concentrically at a distance around a central axis. Each circular ring shell consists of compressor blades (1) and turbine blades (2), arranged side-by-side on a circular ring and connected to each other by means of separator rings (4) and bearing rings, and which have one or several energy aggregates which drive the circular ring shells, so that the surrounding medium is taken up by the circular ring shells, accelerated and again expelled through nozzles (10), whereby the centrifugal ring itself is held rotationally stable with respect to the center axis by an electronically controlled braking device (14) on the counter-running shells or by means of nozzles or through a projecting torque support.

Abstract: A flying saucer is remotely controlled and includes a plurality of angularly spaced apart guide flaps and motors all of which are operated independently of each other. Each of the motors has a fuel tank associated therewith and the fuel tanks can be interconnected with each other to share fuel or can be connected with a main fuel tank to receive fuel therefrom.

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: A vehicle capable of omnidirectional movement employing a jet engine and a plurality of directional jet nozzles communicating with said engine, and a single controller means united with said nozzles to cause omnidirectional movement of said vehicle and control the acceleration and deceleration of said vehicle.