Abstract: A water spray deflector to deflect water spray produced from aircraft landing gear from components of the aircraft. The water spray deflector has an inner diameter and an outer diameter. Coupled to the spray deflector are attachment arms that are adapted to couple with an outer portion of a rim of the landing gear. The attachment arms are also configured to support the water spray deflector position the water spray deflector a distance from a side wall of the tire to prevent the side wall of the tire from coming in contact with the water spray deflector under various loading conditions placed on the tire. In some versions, the water spray deflector is weakened in areas to encourage a failure mode of the water spray deflector.

Abstract: A trimaran type WIG (Wing-In-Ground) effect ship with a minimum waterplane area is disclosed. This WIG ship comprises a main hull and two half-submerged sub-hulls each having a minimum waterplane area capable of minimizing the wave resistance and appendage resistance of the ship, thus reducing speed loss on rough water. The WIG ship also has main and sub-wings and an effective propelling mechanism, designed such that they produce a strong lift force allowing a take-off of the ship sailing on water even at a low speed. The WIG ship is thus excellent in its seakeeping and maneuverability on the rough water. In the WIG ship, the main hull is intermediately positioned between the main wings and comprises a slender and half-submerged body, and bears 60% of the total displacement of the ship. The sub-hulls are respectively provided under the outer ends of the main wings, and each bear 20% of the total displacement, and act as an end plate.

Abstract: The additional device according to the invention for floats for seaplanes and floatplanes comprises four airtight bladders (10) to which compressed air can be applied, and which extend along the float and rest on side surfaces (11) of the float, which essentially consists of a box (1). The bladders (10) are composed of a flexible material with little expansion capability or an elastomer material, and are entirely covered with an elastic and watertight textile skin (9). In the state when compressed air is applied, the edges of the box (1), that is to say the side edges (8) and the keel edge (7), are smoothed. Thus, as soon as the aircraft has become airborne, the drag coefficient cD of the float can be considerably reduced. The compressed air is released for the aircraft to land on and take off from water, so that the edges (7, 8) can produce their effect for directional stability (keel edge (7)) and in order to prevent the Coanda effect (side edges 8)).

Abstract: A floatation system for attachment to a helicopter landing skid includes a girt dimensioned to be attached to a landing skid and a plurality of floats attached to the elongate girt, wherein the plurality of floats are adapted to be converted from a packed configuration to an deployed configuration, and wherein at least one of the plurality of floats extends beneath the elongate girt when the plurality of floats is in the deployed configuration.

Abstract: A twin float aircraft (1) which has a retractable float (4 and 5) for each side of a fuselage (3) providing buoyancy for the aircraft during take off and landing and reduced air resistance during flight with each of the floats (4 and 5) being articulated (12 and 13) to assist streamline alignment when retracted.

Abstract: General aviation class amphibious aircraft which include two fuselages, each having a hydrodynamic surface, the fuselages connected via a primary flight surface and a ducted power plant located aft and above the fuselages. The power plant location removes the fan/propeller arc from water and spray during water-borne taxiing, takeoff and landing. The combination of fuselages, lifting surface and ducting provides an aerodynamically efficient design with a lower center of gravity and protected powerplant for yielding improved performance including increased range and airspeed, together with favorable maneuverability, stability and control characteristics both aerodynamically and hydrodynamically.

Abstract: An aircraft has a fuselage, one or more propellers and a main wing. The wing has a central portion located beneath the fuselage and distal portions which extend outwardly from opposite sides of the fuselage. The wing floats on water when the aircraft is stationary and maintains the fuselage above and out of the water. The aircraft optionally has a tail having a horizontal stabilizer which provides additional support to the fuselage to maintain it out of water. The structure of the aircraft can be adapted for use as a water-craft by reducing the length of the wing.

Abstract: A high altitude low flying platform hull, including a laminar flow airfoil, a first slab side, a second slab side, a first fin and a second fin. The laminar flow airfoil has a nose, the nose has a nose leading edge. The first slab side has a first slab side leading edge and a first slab side trailing edge. The first slab side has a serpentine or s-shaped first slab side leading edge. The second slab side has a second slab side leading edge and a second slab side trailing edge. The second slab side has a serpentine or s-shaped second slab side leading edge. The first slab side and second slab side mate to the laminar flow airfoil. The first slab side leading edge and second slab side leading edge intersect the nose leading edge. The first slab side trailing edge extends upward to create the first fin, and the second slab side trailing edge extends upward to create the second fin.

Abstract: A small wing, located on the inside face of each float of a float airplane that causes the plane to go on step in ⅓ the space normally required. The wings are fixed in place on the floats. The wings enable a plane to take off on much smaller bodies of water. Conversely, the shorter step distance allows a plane to carry more weight than was possible before.

Abstract: A hydrodynamic/aerodynamic amphibious aircraft (1) has a fuselage (10) with sponsons (100) extending outwardly and downwardly on either side of the underbelly (5) to define an inverted channel (15) having a substantially constant cross section. Each sponson has a forward portion (110) fixed to the fuselage and a movable aft portion (120). The aft portion tapers smoothly to a trailing edge (122). When the aft portion is in the flight position the forward and aft portions form a smooth low-drag symmetrical airfoil aerodynamic shape. When the aft portion is raised a hydrodynamic step (112) is left on a lower surface of the forward portion, which turns each of the forward portions into a planing hull.

Abstract: A lightweight, high strength aircraft float for use by ultralight, experimental, and light general aviation float planes. The float consists of a unitary outer shell that is formed into a desired shape using rotational molding, or blow molding, from a suitable polymer. In the preferred embodiment, the shell is manufactured of a high strength, cross-linked high density polyethylene, which has high strength, high impact resistance and is resistant to degradation by ultraviolet light. It is also preferred that an internal reinforcing structure be utilized to provide additional stiffness and rigidity to the upper and lower surfaces of the float. This structure may consist of the two extruded aluminum box sections, formed to appropriate profiles, which are inserted through small apertures at the front or rear of the roto-molded shell and secured within the shell by mechanical fasteners.

Abstract: The invention comprises an improved seaplane having a retractable step. The term retractable step, however, is a misnomer. The step portion of the seaplane float includes a panel which may be extended once the plane is airborne to reduce aerodynamic drag created by such hydrodynamic steps. The panel may be hinged at a rear portion of the aircraft and extended and retracted using a hydraulic strut or the like. Side panels may also be provided which would hinge via a piano type hinge or the like to the sides of the extendable panel. The side panels may be provided with an end pin or pins which would travel in a track within the step cavity such that the side panels would be pushed into position as the step cover panel is extended. The apparatus of the present invention may be employed in both conventional and tunnel type hulls.

Abstract: An amphibious water bomber float plane, wherein the water bomber plane is equipped with a pair of floats for landing and taking off on water, with wheels for use on land, and having pair of floats secured for supporting the plane on water, water tanks within the floats for accumulating water for water bombing, scoops mounted in each float for lowering and raising between lowered and raised positions, and, when in the lowered position, the scoops entering the surface of the water causing water to flow upwardly into the tanks, dump doors mounted in each float, in communication with the tanks, the dump doors being swingable between an open dumping position and a closed sealed position, and controls by which the dump doors may be operated from the plane. Also disclosed is a method of water bombing from an amphibious float plane.

Abstract: A seaplane hull which in one embodiment has a high length to beam ration, substantially fair topside waterlines from bow to stern and a fine bow entry angle is disclosed. These characteristics minimize dispersement of the water, offering the low wave-making drag characteristics which enable high speeds without requiring planing lift. Chines on the underside describe a slim planing surface where edges converge aft toward a central plane. The slim planing surface minimizes wetted area at speed, and low pressure hollows, provided immediately above the chines, allow for air to travel aft and under an afterbody when at speed. The design enables continuity of aerodynamic and hydrodynamic streamlines throughout acceleration to take-off speed.

Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Abstract: A hydrofoil comprising a flat vessel of aerodynamic profile which, together with small planes, produces an aerodynamic lift, and the broad base of the hull contains a set of flexible fins whose cross-sections reduce from relatively thick inner ends of relatively large cross-section to relative thin outer ends of relatively small cross-section, that are fixed at their thicker end, that are inclined toward the end opposite the forward movement of the vessel, constructed and arranged to meet the water at their large surfaces, and to generate a hydrodynamic lift, with air flow propulsion, by the, for example, propeller, turboprop, or turbofan type turbodrive engines in the upper part.

Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Abstract: The transport facility with dynamic air cushion, which has a hull, a wing with flaps, and a tail empennage. A power system turns propellers connected with a transmission. The propellers are installed in front of the wing. Pneumatic cylinders are located at the ends of the wings parallel to the fore-and-aft axis of the transport facility. The engine is installed inside the hull and the propellers, used for a power-augmented ram technique, are driven by the transmission system connected to the engine. Turning pylons connected to the propeller bosses change the propellers rotation plane within the angle (.alpha.=0.degree.-80.degree.). The pylons are installed on the hull. The tail empennage consists of two fins and a stabilizer installed on the fins. A retractable elastic pneumatic ski is installed at the lower bow surface of the hull. The lower surface of the ski, in a release position, is located below the lower surface of the side pneumatic cylinders.

Abstract: A flotation apparatus, specifically a ski (27), is provided for use on an aircraft (21) for improving the egress and ingress from the aircraft cabin (20). The ski (27) is particularly applicable to helicopters (21) having fixed wheeled landing gear (23) wherein the helicopter (21) engages in rope repelling missions or wherein egress and ingress from the helicopter cabin (20) may be performed during low hover operations. The ski (27) includes a forward potion (55) substantially fixed in a parallel configuration with respect to the longitudinal axis of the helicopter and an aft portion (57). The aft portion (57) is rotatable from a substantially parallel configuration with respect to the longitudinal axis of the helicopter to a substantially perpendicular configuration with respect to the longitudinal axis of the helicopter; the aft portion (57) is rotatably attached to the forward portion (55) using a fastener, specifically a hinge means (35).

Abstract: An energy absorbing structural unit is attached outside the fuselage belly of an aircraft having at least two decks arranged one over another. At least the lower deck, of which the floor is adjacent to the fuselage belly, includes passenger cabin compartments and/or service facilities. The energy absorbing structure is an energy absorbing structural unit (5) that is attached outside of the existing aircraft fuselage (2) approximately vertically below the passenger cabin compartment (9) and/or service facilities provided on the lower deck of the aircraft. The energy absorbing structural unit absorbs impact energy arising in a crash or emergency landing of the aircraft. Because impact energy is absorbed by the external structural unit rather than or in addition to the structure of the aircraft fuselage and air frame, it is possible to provide lower deck passenger cabin space that may be continuously occupied by passengers and crew even during the take-off and landing phases of a flight.

Abstract: An amphibious aircraft, capable of high speed maneuverability on the surface of the water, utilizes a aerodynamic platform to generate lift and to define a tunnel with a pair of central sponsons extending inwardly of the wings of the aircraft longitudinally of the platform which supports the cockpit and propulsion system.

Abstract: The invention relates to an amphibian aircraft incorporating a hydrodynamic system formed by three floats wherein the first two floats are attached to a fuselage leading portion symmetrically to the aircraft axis and the third float is attached to a fuselage trailing portion along the aircraft axis of symmetry. The distance between the floats renders it possible to place a trailing float out of the zones of the water surface disturbed by hydroplaning leading floats. Moreover, the center of gravity is shifted behind the steps of the bottom of the leading floats to the trailing portion of the fuselage.

Abstract: A twin-hull seaplane comprising two hulls spaced apart by a suitable distance, a cabin provided on the hulls integrally therewith, a front wing and a rear wing provided on the cabin and having a length not greater than the width of assembly of the two hulls or foldable to a length not greater than the width, aero-propulsion engined mounted on the front wing or the cabin, and a rudder attached to the rear wing. Each of the hulls is provided with hydro-propulsion means at a rear portion thereof.

Abstract: An amphibious aircraft capable of V-STOL operations, the aircraft comprised of a pair of buoyant, coterminus, and elongated body members having an axially converging and diverging profile, joined together at the forward end thereof by a forward fuselage having at least one cambered surface, the entire structure thereof functioning as a lifting body, the forward fuselage having a pair of wings rigidly attachable thereto, and at least one propulsion unit attachable thereto proximal to the aircraft's longitudinal centerline, whereby the transition between vertical and conventional flight modes may be accomplished, the aircraft further having a stabilizer for pitch and yaw control which are pivotally and hingedly attachable to the rear of said elongated body members.

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.

Abstract: A flying boat or sea plane has a wing system in order to obtain hydrodynamic lift when protracted and including two wings arranged one above the other but establishing, in front view, a closed frame; the wing system can be retracted into the fuselage of the vehicle by turning the wings upside down and pulling them into the fuselage using a three-group lever system.

Abstract: A seaplane having a low wing, a cabin over the wing, a pusher propeller located at the aft end of the cabin and just forward of the trailing edge of the wing and an empennage supported on a tail boom. The central portion of the leading edge of the wing extends forward in the shape of an isosceles triangle with its base against what would be a conventional leading edge and its apex in a vertical plane through the center line of the aircraft. The wing, including the triangular extension, provides flotation. The underside of the central portion incorporates transverse, angularly displaced and longitudinal steps. The lower portion of the propeller arc is separated from the water surface by the thickness of the wing near its trailing edge and the clearance between the arc and the proximate upper surace of the wing, allowing the thrust line and line of action of aerodynamic drag to be relatively close, resulting in a relatively low negative pitching moment.

Abstract: An inflatable external fuel tank is disclosed for carrying fuel under an aircraft wing, the tank having a predetermined displacement when full and being collapsible to a lesser displacement when empty. The tank skin is comprised of a flexible thermoplastic material. A keel structure is located inside the tank and defines the diameter and longitudinal length of the tank.

Abstract: An aero marine vehicle having a fuselage having front wings extending from its respective left and right sides. Engines are mounted in these wings and their drive propellers are supported adjacent the rear edge of these wings. A pair of laterally spaced hull members are supported beneath the respective right and left wings. A plenum chamber is formed in each of the hull members with the bottom wall of the hull members forming the bottom wall of the plenum chambers. Exhaust lines are connected between the engines and the respective plenum chambers. The bottom wall of the hull members has a plurality of exhaust ports formed therein which allow the escaping exhaust gases to form a boundary layer of air between the bottom wall of the hull members and the water they are floating upon to overcome the suck-down effect of the water upon the hull member. The majority portion of the interior of the hull members form a buoyancy chamber.

Abstract: A ground effect vehicle consists of a central, wing-like support body (1), floats (5) and/or undercarriage units located on both sides of the support body, a thrust generator (11) located in front of the support body, a control surface (14, 16) and a cabin (17), located on top of the support body for at least one person and, if required, for payloads. In order to increase the ground effect and to realize the ground effect even at low speeds, a nose (6) extending far forwards is provided in front of the support body (1), which nose forms an airflow duct (7) directed under the support body, the thrust generator (11) being located under the front region of the nose (6) in or immediately in front of the airflow duct (7).

Abstract: A surface effect vehicle comprises a hull of a generally rectangular shape concave at the front underside and contouring to a flat planing hull at the stern, an upper surface forming an airfoil, a passenger/operators cabin is mounted on top of the hull and support a ram wing and propulsion system.

Abstract: An amphibious executive or business airplane, also having military application, possesses sponsons integrated with the airplane fuselage. The trailing end of the sponsons end in a sharp edge, thus eliminating the need for a hull or float step or venting. A channel is formed by the sponsons and the underside of the fuselage, which channel has a constant cross-section and produces a surface lift effect facilitating take-off and landing. A pair of keels beginning substantially aft of the center of gravity of the airplane provide directional stability on the water. The aircraft is preferably jet powered with the inlet of the engines disposed above the sponsons to eliminate water intake. Variable geometry wings of telescoping design maximize aerodynamic performance on take-off and landing and during the high altitude, high speed cruise regime of the flight.

Abstract: A transient air and surface contact vehicle for transporting a person has a fuselage structure for carrying a person. A vehicle support extends from the structure and abuts a surface and thereby supports the vehicle at a predetermined distance above the surface. A buoyancy control device mounted on the structure and on the vehicle support provides for the buoyancy required to keep the vehicle afloat while stationary and at low speeds. At high speed the dynamic pressures generated at the bottom of the struts provide the supporting forces. A power source is mounted on the structure for moving the vehicle along the surface at the predetermined distance above the surface. A position control mounted on the structure produces a positive pitching moment to cause the vehicle to become airborne, a negative pitching moment to maintain the vehicle in surface-following contact with the surface and both moments to control the altitude of the vehicle when it is airborne.

Abstract: Propellers are provided to drive a vehicle or to bear a vehicle in air. Such propellers have commonly been fixed to wings or fuselages. The fixed locations of the propellers limited the abilities and capabilities of the respective vehicle. The invention now provides arrangements on or to propellers which makes it possible to change the location of the respective propeller relative to another portion of the vehicle. The change of the location of the propeller in relation to another portion of the vehicle makes it possible to improve the abilities or capabilities of the vehicle. Specifically beneficial effects are obtained by applying the invention to propeller-pairs. Specific relations of locations of propellers to wings or to flow of air in combination with means to pivot portions of the arrangement(s) can lead to better overall efficiencies, speeds, bearing capacities, economy or comfort of the vehicle or of portions thereof.

Abstract: A helicopter flotation pack includes an inflatable flotation bladder secured to an intermediate structural member which includes means for attachment to a helicopter landing skid. The structural member cooperatively defines a sheltered chamber for inflation apparatus and also carries an environmentally protective cosmetic cover which advantageously directs the deployment of the flotation bladder during inflation. The nature of the interconnection between the inflation bladder and structural member is such that both in-flight stability and flotation load-bearing capacity of the flotation bladder are increased.

Abstract: An apparatus is provided for an amphibious aircraft which also has retractable landing gear. The apparatus senses changes in aircraft speed indicative of an imminent landing or a takeoff and prompts the pilot to verify that the landing gear is in a position compatible with the type of surface, land or water, chosen for landing.

Abstract: A transient surface contact vehicle for transporting a load from a surface starting point to a surface end point has a structure for carrying the load from the starting point to the end point. A vehicle support extends from the structure. A buoyancy control device mounted in the structure is coupled to the vehicle support for selectively making the support buoyant and non-buoyant whereby when the support is buoyant it abuts the surface of a body of water thereby supporting the vehicle at a predetermined distance above the surface of the body of water. An acquisition sensor mounted on the structure initiates water surface operations. A sensor is mounted on the structure and cooperates with the acquisition sensor to energize upon tracking of the target and to move the vehicle along the water surface to impact with the target at the end point. A position control mounted on the vehicle produces a negative pitching moment to maintain the structure in surface-following contact with the body of water.

Abstract: Propellers are provided to drive a vehicle or to bear a vehicle in air. Such propellers have commonly been fixed to wings or fuselages. The fixed locations of the propellers limited the abilities and capabilities of the respective vehicle. The invention now provides arrangements on or to propellers which makes it possible to change the location of the respective propeller relatively to another portion of the vehicle. The change of the location of the propeller in relation to another portion of the vehicle makes it possible to improve the abilities or capabilities of the vehicle. Specifically beneficial effects are obtained by applying the invention to propeller-pairs. Specific relations of locations of propellers to wings or to flow of air in combination with means to pivot portions of the arrangement(s) can lead to better overall efficiencies, speeds, bearing capacities, economy or comfort of the vehicle or of portions thereof.

Abstract: This invention provides a new form of landing gear for a water plane that will minimize the time and power required to accelerate it from the at-rest, displacement-borne phase to the planing phase and takeoff phase of its operation. The landing gear of the invention is of hydrofoil type and separates the buoyant support function from the planing support function and recombines them in a way which causes them to interact, mutually assisting each other in all phases of operation, simultaneously providing a much lighter and stronger structure, having less drag and requiring less power input than devices and combinations heretofore used or proposed. Thus, the plane body is of any suitable water borne hull shape with two wings whose roots are submerged while floating to give transverse stability.

Abstract: A boardsailing device includes a sport converter which permits the boardsailing device to be converted into a hang glider. Essentially all of the power required for hang gliding is supplied by boardsailing, and the conversion from boardsailing to hang gliding is executed during boardsailing.

Abstract: A surface-effect aerofoil boat having two aerofoils arranged in tandem and having a gap for a propulsion or air screw between a vertical fin and an aerodynamic rudder and wherein the aerofoils are designed as hollow bodies subdivided into compartments some of which being provided with flooding and emptying devices. The rear aerofoil seen in the direction of travel is clipped with respect to the geometry of its trailing edge in a polygonal or rounded-off manner. The gap in the plane of rotation of the propulsion or air screw is widened in its radially outer zone relative to the inner zone near the axis.

Abstract: An aircraft tire having a liquid deflector extending outwardly from at least one sidewall, a first plurality of grooves in the tread and a second plurality of grooves disposed axially outwardly of the tire relative to the first plurality of grooves for directing water from the first plurality of grooves toward the respective liquid deflectng means. The first plurality of grooves may interconnect to direct water to the second plurality of grooves each of which may extend at an angle of between about 25 and 35 degrees relative to a radial plane of the tire passing through the respective groove.

Abstract: A ski/float landing gear is flexibly constructed of a resin reinforced with fiber. The ski/float has a pneumatically inflatable upper member, which is molded to fall to a flat shape when deflated. Engine exhaust gases are used to inflate and deflate the float. Air discharged from the lower side of the ski portion provides a boundary layer effect. The use of engine exhaust gases gives the ski element a rapid thaw capability in freezing weather.

Abstract: Aircraft safety apparatus includes front and rear parachutes mounted at the front and rear portions of the aircraft for adding to the buoyancy thereof during emergency landings. Devices are provided for moving the parachutes into their operating positions. A plurality of auxiliary jet propulsion units containing fluid under pressure propel the aircraft to aid in its manueverability should the aircraft malfunction in flight, as well as during emergency landing procedures. At least some of the jet propulsion units are directed transversely to the body of the aircraft to direct fluid under pressure laterally to cause lateral reaction movement of the aircraft for steering purposes while the aircraft is descending under parachute assist.

Abstract: There is disclosed an airplane having an inflatable type air cushion confining undercarriage thereunder wherein the airplane wing structures comprise three-dimensionally enlarged inner wing components merging aerodynamically with the airplane fuselage. The under surfaces of the inner wing components and the fuselage cooperate to provide a downwardly convex broad base structure which is oval-shaped in planform, and a toroidal configured inflatable trunk is attached to the perimeter of the base structure for circumscribing the air cushion cavity under the airplane. Thus, an enlarged width and length air cushion type undercarriage is provided to give the airplane improved stability characteristics when operating in air cushion, ground, or water supported mode. When the trunk system is deflated the elastic sheet material thereof retracts snugly against the slightly convex bottom surface of the base structure.

Abstract: A substantially spherical human living module or space has a plurality of pontoons projecting from its lower hemisphere. It is preferably arranged to be self-propelled, as a vehicle, and the pontoons are preferably extensible and retractable. In a version in which wheeled landing gear is provided, a spherical human living space is provided with helicopter blades and four jet engines at the bottom of the craft, and two jet engines on the right and left sides, which swivel for direction control, for propelling the device.

Abstract: A float assembly for supporting a vehicle having three cylindrical float tubes tangentially secured together by a suitable adhesive with two of the float tubes being positioned so that the centerlines thereof are in a horizontal plane. The three float tubes are secured together to form a pyramid whereby the intersections thereof form a Y-shaped cross-sectional configuration so that the centers of the cylindrical float tubes form a triangle which is or approaches an equilateral triangle. Girths are secured to the float assembly in the horizontal plane and are suitably bolted to skids which are attached to the vehicle. The forward and aft ends of each of the cylindrical float tubes are frustoconical shaped cones which are inclined upwardly to increase the maneuverability of the vehicle and prevent pitch poling. The outboard and top float tubes have bulkheads to provide several sections to enable the float tubes to provide flotation in the event that one of the sections is deflated.

Abstract: A surface vehicle has two wings, which are hinged to a wing core along axes extending along the wing center axis, to change the angle of attack, so that the trailing wing edges as extending towards the rear in converging configuration remain in a common plane and close the plenum chamber with reference to the (hypothetical) mirror image of the wing construction.

Abstract: A ski device adapted to be mounted on a landing gear provided with front and rear sheets each of which carry a wheel with the wheels being positioned in tandem. The device includes a monobloc ski assembly having an aperture therethrough through which the wheels move to raise and lower the skis off the ground and provide for ease of manoeuverability on a runway and a snow covered terrain.

Abstract: A water-based sailing vehicle that is able to accelerate from rest under wind power, become airborne, and fly above the water. At low speeds, the vehicle performs as a displacement sailboat. At higher speeds, the weight of the vehicle is supported by a combination of hydrodynamic lift from the planing hull and aerodynamic lift from the wings, or by aerodynamic lift alone. The wings are set at a large dihedral angle, so that with one wing-tip float immersed, the horizontal wing provides a lifting force, while the raised wing provides a horizontal side force for sailing, plus some additional lift. The wings and tail have airplane-type control surfaces which give complete control both in the sailing mode and in free flight.