Abstract: A capacitor unit used as an auxiliary power source is structured by a plurality of series connected capacitors that have an initial dispersion of characteristics controlled within a predetermined value. During charging, the capacitor unit is monitored if a voltage of the entire capacitor unit is not exceeding a predetermined value. This prevents each capacitor from being charged at a voltage exceeding a withstand voltage.

Abstract: The present invention is an air cushion vehicle and a control mechanism for steering and turning the vehicle. The air cushion vehicle includes a frame having a skirt body extending around the perimeter. An air flow generator may be positioned on the frame for providing a lift flow and thrust flow. At least one vane is disposed on the frame to direct the thrust flow. At least one fin is disposed on the frame downstream of the vane for directing the thrust flow. A turning controller may be used for moving the vane and fin in a coordinating movement to affect the direction or the motion of the air cushion vehicle.

Abstract: An air-based thrust recovery system for use in a powered lift platform utilizing fixed-pitch propellers is provided. The system utilizes an air compressor coupled to the drive motor of the platform and an on-board, high pressure tank for air storage. The fixed-pitch propellers are coupled to the primary drive system with over-running clutches, thus allowing the thrust recovery system to rotate the propellers faster than if driven solely by the primary drive system. Preferably the propellers are surrounded by air ducts. The thrust recovery system uses individually, or in combination, cold air jets mounted at the tips of the propellers, a circulation control system which blows out the leading or trailing edge of the propellers, and one or more perforated tubing segments surrounding at least a portion of the platform's air ducts.

Abstract: A “wing in ground effect” aerial vehicle includes a wing mounted on a fuselage, and two cycloidal propulsion units for providing lift, thrust and longitudinal control. Additional lift is provided by a lighter-than-air gas such as helium contained in the fuselage. Operationally, the two cycloidal propulsion units and the volume of lighter-than-air gas are concertedly regulated to achieve “wing in ground effect” flight. Importantly, the two cycloidal propulsion units may operate in one of several modes, to include a curtate mode, a prolate mode, and a fixed-wing mode. Additionally, the vehicle may hover. Also, a thruster unit is mounted on the fuselage for providing forward thrust in combination with, or in lieu of, the two cycloidal propulsion units.

Abstract: An air board including a platform upon which an operator of the vehicle can be supported; and a support arrangement for providing an air flow for supporting the platform above a surface, wherein the direction of movement of the air board is at least partially controlled by varying the weight distribution of the operator on the platform.

Abstract: A multi-modal forced vortex device is described having a top plate and a side wall creating a partially enclosed volume. The top plate includes one or more adjustable fluid openings to permit, or restrict, fluid flow into and out of the partially enclosed volume. Rotating blades housed within the partially enclosed volume are manipulated (through control of their pitch and, possibly, their speed) in conjunction with the adjustable fluid openings to generate a variable magnitude attractive force in a first mode, a variable magnitude down or pushing force in a second mode, a variable magnitude up or lifting force in a third mode or variable magnitude yaw, pitch and roll forces in a fourth mode.

Abstract: The invention is a marine wing-in-ground effect vehicle capable of sustained high speed operation in varying seas. The vehicle comprises an aerodynamic flat bottom lifting wing with a fuselage, a longitudinal keel member under the wing, a propulsion unit installed in the keel member, a vertical stabilizer airfoil mounted on top of the wing, and an overturn prevention tail at an aft end the wing. Port and starboard surface foils are pivotably mounted under the wing, and taper from a wider front end to a substantially narrow trailing end. The surface foils are selectively and independently pivoted between a deployed position and a retracted position by an actuator.

Abstract: A displaceable support stand (1) includes a support stand base (5) with a support surface (6) which is adapted to rest on the ground, a lifting device for lifting the support stand base (5) and therewith the support stand (1) above the ground and a displacement device which permits displacement of the support stand (1). The lifting and the displacement devices can be embodied by a device for producing an air cushion. A device of that kind can include for example a compressor (18), an accumulator (20) for the power supply for the compressor (18) and air nozzles (16).

Abstract: A hovercraft is capable of operation on either a solid surface or a liquid surface. The hovercraft includes a hull on which is mounted at least one thrust-lift fan assembly for providing an air cushion under the hovercraft and for propelling the hovercraft in a forward or reverse direction. The hovercraft also includes a steering fan assembly mounted transversely to the thrust-lift fan assembly and that allows the hovercraft to be steered in any lateral direction. The hovercraft is controlled by operation of the fans in the appropriate direction, and may be in the form of a wireless remote control toy.

Abstract: A robot cleaner capable of returning to an external recharging device.

Abstract: A personal transportation apparatus has a frame defining a surface for supporting a load, and a plurality of air-cushion cells mounted to the frame and depending from a lower side thereof, the air-cushion cells each having a changeable height to accommodate variations in an underlying terrain during a translation of the frame over the terrain. A pressure source is mounted to the frame and is operatively connected to the air-cushion cells for supplying air under pressure to the cells, thereby generating an air-cushion support for the frame. An elevation mechanism is mounted to the frame for lifting the frame from one step to a next higher step of a stairway so that the frame ascends the stairway from a lowermost step to an uppermost step of the stairway.

Abstract: A vehicle is disclosed having a hull with a longitudinal, vertical and lateral axis, the hull further having front end and rear ends and first and second sides. A turbofan engine mounted in said hull, said engine having an exhaust duct. First and second front exhaust nozzles are mounted on the first and second sides of the front end of the hull. First and second rear exhaust nozzles are coupled to the first and second sides of said hull at said rear. All of the exhaust nozzles are rotatable from a vertically downward position to at least a partially horizontal direction and incorporating shudders to adjust the flow rate of exhaust gas from said turbofan engine therethrough. A duct system for coupling the exhaust duct of the turbofan engine to all of the nozzles.

Abstract: The invention relates to a hovercraft, comprising at least one fan for producing an air cushion, and at least one thrust unit, which acts on the top surface (4) of the craft and which is used to propel it and/or to control its direction. Both the fan and the thrust unit have at least one airscrew that is driven by means of a motor (5, 6, 21) and generates an air current. The motor takes the form of an electromotor (5, 6, 21) located directly on the airscrew. At least one central energy generator (7), which supplies the electromotor (E1, E2, A) with driving energy via an energy line (5a, 6a, 21a), is provided in order to generate the electrical driving energy required by said electromotor (E1, E2, A).

Abstract: To secure normal operation and then restart a microprocessor (CPU) when a CPU built into an on-vehicle electronic apparatus runs away. A number of on-vehicle loads driven from a CPU, a watchdog timer for monitoring the CPU to reset and restart it on occurrence of an abnormality, and a memory element for storing generation of the reset output are provided, and load driving elements or a load relay is rendered inoperative by output of the memory element. The memory element is reset by cutting off or reclosing the power switch, and an on-vehicle electronic apparatus returns to a normal state.

Abstract: A surface effect drilling craft or hovercraft is provided for taking continuous core samples in normally inaccessible environmentally sensitive regions such as wetlands. The hovercraft includes an inner hull including an inner hull floor and a bottom hull disposed beneath the inner hull and a base mounting plate secured to the inner hull floor. A drill tube extends through the base mounting plate, inner hull floor and bottom hull. A drill rig including a multi-sonic drill is mounted on the base mounting plate adjacent to the drill tube. The drill rig includes a fixed lower section, and a pivotable upper section movable between an erected, operative position for drilling and a collapsed, inoperative position during maneuvering of the hovercraft. A drill cap is used to close off the drill tube during this maneuvering.

Abstract: A novel drive for a lifting platform utilizing a simple propeller, impeller, or gas turbine is disclosed. The axial air rotation from the drive is eliminated in order to permit the development of a partial toroidal vortex which efficiently maintains a raised air pressure zone beneath the lifting platform. The axial components are eliminated by means such as flow straightening vanes, which may also serve to control lateral motion of the lifting platform. The system can also be easily modified to function as an attractor device. Overall, the present invention explores the effect of vortices, both cylindrical and toroidal, and seeks to optimize their effects.

Abstract: The invention concerns a transport vehicle, comprised of a transport unit and a propulsion unit. The propulsion unit comprises a pressure housing with a plurality of radial turbine wheels arranged on a common shaft and rotating in opposite directions from one another. There are fixedly arranged combustion chambers having nozzles at the radially outwardly positioned ends of the turbine wheels. The invention also concerns a method of operating the transport vehicle.

Abstract: The invention concerns a ground effect vehicle comprising hydrofoils or hydrofoil outer parts (18) which can pivot about a parallel line relative to the longitudinal axis of the body in order to increase the speed range when flying close the ground. In addition, the hydrofoils and the body can be provided with trailing edge flaps (19) which are articulated so as to pivot about a horizontal axis and, depending on the selected angle of incidence of the hydrofoils or hydrofoil parts, can be controlled as lift-increasing ailerons or flippers.

Abstract: A ground effect flying craft utilizing a pressure cavity (10) for low speed support on a static air cushion. The cavity is bounded by a streamlined aft body (18), a fore body (24), and side plates (22) which allow for low drag and high lift at cruise speed on a dynamic air cushion. Static lift pressure and dynamic thrust are provided by a fixed dual purpose propulsor (20'). Flow diverting devices or auxiliary power units are not needed for transition from static lift to dynamic flight.

Abstract: The lift augmented ground effect platform of the present invention is characterized by two pair of annular concentric air curtain nozzles and supercharge nozzles which direct respective jet streams downward and inward beneath the downwardly facing lifting surface of the platform. The concentric arrangement of the nozzles provides an inner or central supercharged air cushion surrounded by an inner central air curtain and an outer or peripheral air cushion surrounded by a peripheral air curtain. The present invention provides an increased or "large" augmentation of the forces acting to raise or lift the platform over that experienced in prior ground effect devices by directing an air flow stream over the downwardly curved peripheral surface of the platform. As the air flows downwardly along the curvature of the platform's peripheral surface, it creates a negative pressure differential which provides an additional lifting force contributing to support of the platform.

Abstract: A method and apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Abstract: The present invention is for a hovercraft load transport assembly which incorporates an air cushion assembly having a fan powered by an engine. The fan draws air into the device downwardly to fill the neoprene skirt of the device. This causes the device to essentially "float" above the ground on a cushion of air. The neoprene skirt is supported on a metal frame. In one embodiment, optional thrust tubes at the back of the device allow for directional movement. Thrust and throttle controls allow for variance in the lift, speed and movement of the device. There is also a load carrying and dumping receptacle which is hydraulically actuated.

Abstract: The lift augmented ground effect platform of the present invention is characterized by two pair of annular concentric air curtain nozzles and supercharge nozzles which direct respective jet streams downward and inward beneath the downwardly facing lifting surface of the platform. The concentric arrangement of the nozzles provides an inner or central supercharged air cushion surrounded by an inner central air curtain and an outer or peripheral air cushion surrounded by a peripheral air curtain. The lift augmented ground effect platform of the present invention provides an increased or "large" augmentation of the forces acting to raise or lift the platform over that experienced in prior ground effect devices by directing an air flow stream over the downwardly curved peripheral surface of the platform. As the air flows downwardly along the curvature of the platform's peripheral surface, it creates a pressure differential which provides an additional force supporting the lifting of the platform.

Abstract: An apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The apparatus a) measures an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmits this actual differential pressure measurement to a computer, c) compares the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed, and d) evaluates performance of the aircraft based on the result of the comparison. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Abstract: The surface effect vehicle comprises a plurality of lift fans for generating an air cushion, each of the fans having a drive with a motor and a regulating circuit with sensors and actuators for acting on the air cushion, each of the drives having an associated regulating circuit, the drive of the first one of the lift fans being operated as a master drive, while a rest of the lift fans being operated as follower drives.

Abstract: A craft for ground effect and aerodynamic flight has, in addition to the usual vertical and horizontal stabilizer(s), a primary, upper airfoil, a lower secondary airfoil and a pivotable flap. The upper surface of the primary airfoil forms the primary lifting surface for aerodynamic flight while the lower surface forms, at its anterior and, an air intake for the compressors powering the craft and, to the rear, the upper surface of a plenum for ground effect flight. The upper surface of the secondary airfoil forms the lower surface of the compressor air intake at its anterior end and a compressed air exhaust at its other end. The lower surface forms the anterior end of the plenum when the pivotable flap is in the down position. The pivotable flap is attached near the forward end of the lower surface of the secondary airfoil to block the flow of compressed gases out the front of the craft during landing and while in hovercraft mode. Preferred models have a vertical stabilizer forward of the cockpit.

Abstract: A surface effect vehicle for traversing a water or ground surface is provided. The surface effect vehicle comprises an elongate body and forward and rear scoops, preferably having a large angle of attack inducing stall conditions on the scoops. Each scoop has an arched leading edge defining, in conjunction with the surface, a forwardly facing opening. Preferably, each scoop also has an opening with a fan mounted therein. Forward and rear skirts are movably mounted relative to the forward and rear scoops. Propulsion apparatus are provided for moving the surface effect vehicle across the surface. When the forward and rear skirts are placed in extended positions covering the forwardly facing openings and the front and rear fans are activated, the surface effect vehicle may be lifted relative to the surface to be traversed.

Abstract: Trim compensation for a hovercraft having two engines (2,3) with flow outlet apertures. The two engines (2,3) are arranged laterally at the stern of the hovercraft to generate air jets for forward motion. The hovercraft also includes a compressor to generate an air cushion beneath the hovercraft. The trim compensation includes a tail plane arrangement located in the air jets in the two engines for directional control of the hovercraft by deflection of the air jets. The tail plane arrangement consists of a negatively arranged V-plane (7) with a middle upper section from which extends stabilizer surfaces (9,10) at both sides in a downward direction. The stabilizer surfaces (9, 10) are provided with rudder elements (11, 12) which are swingable in the same or opposite direction to deflect the air jets. The stabilizer surfaces (9, 10) and the rudder elements (11, 12) run centrally across the flow outlet apertures of the engines (2, 3).

Abstract: A steering device for a hovercraft having two driving engines (2, 3), a back skirt (5), a finger skirt (6) and a jet deflection device located downstream of the two driving engines (2, 3). The jet deflection device includes a negative Vee stream deflector (7) and rudder elements (11, 12) which can be operated in opposite directions. The Vee stream deflector (7) is arranged behind the driving engines (2, 3) in such a way that each driving engine (2, 3) is assigned a portion of the Vee stream deflector (7) having the rudder element (11; 12). The rudder elements (11; 12) run diagonally through an axis of symmetry of the respective driving engine (2, 3). The Vee stream deflector (7) further includes a middle section which acts as a stabilizing nose (8).

Abstract: A desired value for the yaw velocity or the difference between the wheel speeds of the undriven wheels is determined with the aid of a linear single-track model using the steering angle and the vehicle speed. This desired value is compared with the corresponding actual value and the controlled variable for the adjustment to the engine torque is obtained from the comparison. To avoid unnecessary control operations, the single-track model has connected to its output an all-pass element which matches the phase rotation of the response of the single-track model at high frequencies to that of the vehicle.

Abstract: A delta wing form body is provided having a central forward apex as well as rear opposite side apices. Each apex includes a vertical powered fan duct assembly extending therethrough and the rear of the wing form body includes forward thrust developing horizontal fan duct assemblies while the center of the body includes laterally and longitudinally shiftable weight structure for omnidirectional shifting of the center of gravity of the wing form body. The center and opposite side fan duct assemblies open downwardly into central and opposite side downwardly opening longitudinal tunnels, respectively, each including retractable and extendable front and rear flap assemblies. The wing form body also includes rear forward thrust developing propulsion fan duct assemblies and all of the fan duct assemblies are variably speed driven from a single power source.

Abstract: A method and apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Abstract: A self-propelled ground effect machine having an elongated body, on the underside of which is an air plenum chamber, and a motor driven fan for directing air flow to the air plenum chamber and for propelling the machine across land or water. The fan is disposed in a cylindrical shroud whose flow axis is generally parallel with the longitudinal axis of the elongated machine body. The axis of the shaft of the rotating fan is mounted at an inclined angle relative to a vertical plane passing through the longitudinal axis of the machine. A splitter device directs part of the air flow into the air plenum chamber and part generally rearwardly of the machine.

Abstract: A small-sized air cushion vehicle includes a hull having a planar bottom surface with an upstanding lower flange disposed at a predetermined angle with respect to the bottom surface. A plurality of apertures are formed in the peripheral flange. An upper hull is mounted on the lower hull and includes a centrally located occupant area. The upper hull engages the lower hull to form a hollow plenum chamber extending internally around the periphery of the upper and lower hulls. A plurality of inflatable members are mounted on the exterior surface of the peripheral flange and are each disposed in fluid flow communication with an aperture in the peripheral flange. A motor driven fan is mounted on the upper hull and directs a portion of an air stream rearward of the vehicle to propel the vehicle and another portion of the air stream into the plenum chamber to inflate the inflatable members and to lift the vehicle a short distance above an underlying surface.

Abstract: A floatable ground effect vehicle is provided with at least one wing arrangement, at least one thrust generator (10) seated in front of the wing arrangement and at least one airflow duct (14) from the thrust generator (10) which can be directed under the wing arrangement. So that the ground effect vehicle can also be designed for a larger number of passengers, the central region of the vehicle is designed as an elongated cabin (2) which is seated on a boat-type float or is itself design as the boat hull. Stub wings (3) arranged on both sides and distributed at equal distances are provided over the length of the passenger cabin (2), the stub wings enclosing a static pressure build-up space on their lower surface. At least one separate thrust generator (10) is installed in front of at least some stub wings (3), the thrust generator being connected or connectable to the respective static pressure build-up space by means of an airflow duct (14).

Abstract: A surface effect vehicle having a pair of lifting scoops, or air foils, mounted on a vehicle body, one in front and the other in the rear. Each lifting scoop has an arched leading edge to collect air under the scoop to lift the vehicle on a cushion of air. The vehicle having a pusher-type engine with a propeller to push the vehicle. There are louvers in the lifting scoops to regulate the height the vehicle travels on a cushion of air, and non-trip appendages on the tips of the lifting scoops to aid the scoops in lifting the vehicle from a surface.

Abstract: An air cushion vehicle having improved maneuverability is produced by providing air discharge vents for diverting at least a portion of the pressurizing cushion air from the side of the volute housing opposite that to which the vehicle is being turned, and discharging it from a thruster at said opposite side in a direction away from the direction of the turn. The thruster is located at a forward position, above the deck of the vehicle and adjacent the centerline thereof, and the discharged air produces a thrust which causes the vehicle to roll in the direction of the turn and permits cushion air to escape from beneath the vehicle at said opposite side, producing a thrust complimentary to the thrust from the volute housing.

Abstract: A combined propulsion and lift unit for an air-cushion vehicle is provided comprising an elongate shaft mounted for rotation about its central longitudinal axis, bearings for rotatably supporting the shaft, an axial wheel with two or more blades mounted on the shaft for rotation therewith, a first housing extending peripherally about the shaft, the housing provided with an air inlet and an air outlet, a drive device connected to the shaft for rotating same at a selected speed, a centrifugal fan wheel mounted on the shaft for rotation therewith, the fan wheel provided with an air inlet, the fan wheel located inside the first housing, and a second housing extending about the perimeter of the axial wheel and the first housing, the second housing having a larger diameter than the first housing thereby defining an air passageway therebetween, the second housing provided with an air inlet and an air outlet.

Abstract: A simple and low maintenance Ride Control System (RCS) for Air Cushion Vehicles (ACV) is presented. This RCS reduces the effect of water wave generated pressure pulses on ACV ride by venting the pressure pulses from the pressurized supporting gas cushion and/or restricting gas flow into a powered blower that supplies the pressurized supporting gas cushion as the pressure pulses occur. The preferred embodiment utilizes high aspect ratio low moment of inertia vanes that are individually driven by brushless electric servo motors and the vanes can rotate in either direction through 360 degrees. A vane braking and locking mechanism is presented that brakes and locks the vanes in a closed position in the event of power failure to the vane drive motors. A further feature of the invention is a venturi that is positioned between the powered blower and the pressurized supporting gas cushion to reduce the effect of the pressure pulses on blower operation.

Abstract: A near surface vehicle including a vehicle body including a nose section having a canard with lift and pitch control. The vehicle body including a cockpit or cabin with a main wing mounted adjacent or above the cabin and including ailerons for lift and roll control. The vehicle body further including a tail section having a tail surface and a thrust air fan for providing air for lift and propulsion of the vehicle. The vehicle including an air diverter for deflecting air into a controllable lift area for initial lift and air deflectors or rudders for controlling vehicle direction and vehicle reverse thrust.

Abstract: This invention makes use of a pressure sensor, which is installed on the wing's surface of the aircraft, to sense the varied air pressure which comes from ground-effect on the wing's surface. A control apparatus is comprised of pressure sensor, a device of signal treatment and the device of elevator control. This apparatus solves the problems of excessively low ground-effected flying altitude and low efficiency of the whole aircraft.

Abstract: A simple, low cost, and reliable, normally cyclic, fluid control valve that in preferred configuration includes one or more rotary valve elements where such valve elements have openings that align with each other and/or with a flow passageway thus forming an aperture for fluid flow during valve cycles. Rotary valve elements may be oriented in different directions to connecting ducts and may have a variety of shapes with a preferred shape being cylindrical. Simple motors drive rotary valve elements such that a rate of valve cycling and/or amount of aperture can be easily controlled by a controller such as a microprocessor. Easy valve servicing and installation are other features. Dynamic sealing of the fluids is preferably accomplished by use of simple low cost labyrinth seals.

Abstract: A hybrid electric vehicle (10) capable of ground travel and air travel is described. The vehicle provides for movement over the ground by wheel motors (20) mounted at each of four ground engaging wheels (14 and 16). The wheel motors are supplied with electric power by a battery pack (24) or an electric generator (32) powered by a combustion engine (22). The combustion engine is also geared to vertically oriented ducted fans (40) and a horizontally oriented ducted fan or propeller (76) for providing the vehicle with the capability of travel through the air. Pressure jets (62), supplied with compressed air from a compressor (66) driven by the combustion engine, augment the lift of the ducted fans and provide steering for the vehicle. The vehicle can also be provided with photo-electric cells (82) for supplying a portion of the electric power for the vehicle.

Abstract: A hovercraft is described having a fan mounted to rotate about a vertical axis. The airflow from the fan is directed to the skirt to create lift and to horizontally aligned outlets to positively propel the craft in both forward and reverse directions and, if necessary, provide a braking force. A valve arrangement is provided to alter the relative airflow between the different horizontally aligned outlets.

Abstract: A flying hovercraft and ground effect vehicle design. The flat double-wing design for small, medium, and large cargo or military transport vehicles allows travel from very slow to medium to high speeds over water or land. The highly elongated, flat wing of very low aspect ratio provides a vehicle that is capable of traveling in ground effect flight at a safe distance above the water. Primarily a high-speed (150-200 kts), over-water, ground-effect, vehicle that is augmented with hovercraft capabilities for acceleration to flight speed, deceleration, and slow to moderate speed (0-75 kts.) operations. The vehicle design is adaptable from one-man units to large, ocean-going high-speed cargo ships of 400 feet and over, with carrying capacities over five million pounds. A vehicle of this design is 250% more efficient than modern aircraft, 15 times faster than cargo ships, and capable of going into true flight to overfly land masses for ocean-to-ocean and inland lake or river access.

Abstract: A surface effect vehicle has a propulsion and guidance system comprising a thrust generator (2) for producing a flow of fluid, a duct (7) adapted to receive the flow of fluid from the generator (2) and to conduct this to an outlet opening (11), a pair of rudders (14) mounted on opposite sides of the outlet opening (11) so as to be angularly adjustable relative to the outlet opening (11) to vary the extent to which they obstruct the outlet opening (11), and a rudder control system (17, 18, 19, 33, 34) adapted to move the rudders (14) together in the same sense between extreme angular positions in which the air flow is deflected to one side or the other of the outlet opening (11), wherein the rudder control system is adapted to move the rudders (14) in the opposite sense to one another so that they close together across the outlet opening (11) and thereby cause the fluid flow therefrom to be substantially progressively reversed.

Abstract: A hovercraft includes a hull having a plurality of diffusion apertures and air skirt for providing a supporting air cushion. An engine drives a propeller which produces an airflow. A movable elevator dynamically divides the propeller airflow between lift and thrust components. A pair of rudders are supported within the thrust component to provide steering.

Abstract: Noise due to the rotation of the air propeller or fan of an air-cushion vehicle is reduced by: 1) reducing the cross-sectional area of the interior of a duct encompassing the fan on the downstream side relative to the upstream side; 2) using wide-chord fan blades of chords increasing from blade root to tip; 3) using a duct and a nose cone on the hub of the fan both having a sound-absoring structure; and 4) mounting the engine and the duct on a common rigid support base and reducing to a minimum the tip clearance between the tips of the fan blades and the duct inner wall surface.

Abstract: A flight system capable of passively stable hover and horizontal translatory flight, comprises an apparatus defining a vertical axis, and including multiple ducts with substantially vertical axes in hover mode, spaced the axis; fluid momentum generators in the ducts to effect flow of fluid downwardly in the ducts in hover; and fluid flow deflector structure in the path of the flowing duct fluid, and angled to deflect the fluid flow away from the axis, in such manner as to provide stability in hover of the apparatus, as well as stability when the entire device is tilted through approximately 90.degree. to execute horizontal translatory flight.

Abstract: An improved ground-surface-effect winged craft has a main body in the shape of an airfoil, side plates extending nearly vertically at the opposite lateral sides of the main body for intercepting air flowing outwards from the underside of the main body, side plate floats provided at the side plates, a float provided at a central lower portion of the main body, an operator's seat provided on the float, vertical and horizontal tails provided at a rear portion of the main body, and a propelling device for lifting and propelling the airframe of the craft by making use of both a power augment ramwing effect with the horizontal tail and a ground-surface-effect generated between the main body and a flat surface such as a water surface or a ground surface.