Abstract: A stabilization system for a towed aerodynamic body 1. The body is provided with two, contra-rotating tubular shrouds 3, 4 each fitted with a set of vanes 5, 6. When the towed body is disturbed by the towing aircraft's wake, the gyroscopic inertia caused by rotation of the shrouds exerts a damping effect on the subsequent oscillatory motion of the towed body. In one embodiment, the shrouds are coupled by wheels which constrain the shrouds to rotate in opposite senses. Hence gyroscopic precession effects due to each rotating shroud cancel.

Abstract: A space launch system and a space transfer vehicle useable within such system. The space transfer vehicle includes a primary propulsion engine and attitude control system powered by the same storable bipropellant fuel and a guidance system for both the atmospheric launch vehicle and the space transfer vehicle. The space transfer vehicle is fuelable in space and has a primary propulsion engine which is configured for variable thrust burns.

Abstract: A submarine is steered by means of a special bow assembly. The submarine has a body formed with a contoured surface and a forward portion forming a bow. The assembly comprises an annular member surrounding the bow with an outer surface complementary to the contoured surface of the body, and actuating means secured to the body for movement of the annular member forward and away from the bow at an angle to the longitudinal axis of the vehicle. When the annular member is displaced at the angle, the vehicle is caused to turn in the direction toward which the annular member is turned.

Abstract: A hydraulic damper is designed, for example, as a piston/cylinder unit. The arrangement has a part (for example, a piston) forming a vibrational system by means of a spring. Vibrations acting on the damper arrangement are greatly attenuated virtually only in the resonant range of this vibrational system, because only in this case can vibrations of high amplitude be excited and a high dissipation of energy by way of hydraulic flows in channels and between cylinder chambers take place.

Abstract: A pontoon boat comprising elongated flotation units of generally circular cross-section positioned in spaced-apart parallel relationship with each of the flotation units having planing fins extending longitudinally of the inboard and outboard sides of the flotation units near the bottom thereof to cause the pontoon boat to readily hydroplane. A wedge-shaped fin is provided on the underside of the outboard planing fins near the bow section to provide additional lift when turning at high speeds to improve control and stability on turns.

Abstract: Marine propulsion apparatus comprising an engine mounted within a buoyant enclosure, which is adapted to be connected to a marine vessel, which requires propulsion. The engine drives a propeller through a simple drive system. The apparatus is adapted to be fitted into position on pivotal mountings for steering purposes, and may itself be fitted with steering apparatus such that it may be maneuvered independently of the marine vessel for positioning relative to it. The enclosure is sized to permit access around the engine for in-situ maintenance and repair.

Abstract: A buoyant boat with a girder box is provided. The girder box maintains the deck part and hull part of the boat in predetermined spaced apart relation and allows the transmission of forces and stresses along the length of the boat. The girder box further enables an outboard engine or an inboard engine in the form of a propeller or hydrojet to be provided. A relatively resilient buoyancy part is provided in accordance with the structure of the invention which extends peripherally of the hull and deck parts to advantageously prevent entry of water into the boat while providing the advantages of design variability, stability and puncture resistance over inflatable structures.

Abstract: A swivel on a string is attached to the windward face of a pinwheel turbine. The other end of the string is attached to the aft portion of a kite thus creating a kite tail. Wind against its veins and leeward parts stabilize the pinwheel's orientation and cause it to spin. The pinwheel is light but tends to produce drag proportional to the velocity of the wind, thereby, stabilizing the kite in both low winds and high winds. A multiplicity of pinwheels can be attached in series on one kite tail, and one or more such kite tails can be attached to a kite to provide directional stability. This self-regulating tail can be used to help keep a kite airborne in an extremely wide range of wind speeds.

Abstract: A pedal boat for recreational use includes an inflatable ring on top of which is mounted a platform structure carrying a seat, pedals and a steering mechanism. The pedals drive a shaft mounted diametrically of the ring and carrying paddles. The steering action is effected by clutching the left or right paddles on the drive shaft.

Abstract: A float having a substantially prismatic and preferably parallelepipedic body, which has corner edge portions provided with corner-connecting elements having eyes and recesses for receiving and interlocking with connecting bolts for connecting a plurality of identical floats in an assembly. In order to increase the strength and stability of the joints between such floats in an assembly consisting of a plurality of layers of such floats, the body of the float is formed at its center with a vertical retaining opening. The opening is adapted to receive a connecting bolt and contains a recessed bearing surface that is engageable by such bolt, a plurality of identical ones of said floats are adapted to be arranged in a plurality of layers in an assembly.

Abstract: A support system for the aft end of fan jet gas turbine engines which reduces engine bending in operation while accommodating radial and longitudinal thermal expension forces. A first radial ring secured to the engine structure core cowl and the overall engine support pylon has a plurality of spaced longitudinal grooves. A second, cooperating radial ring secured to the engine has a plurality of outwardly extending tabs sized to fit within the first ring grooves. The tabs do not extend fully into the grooves at ambient temperatures. When operation of the engine begins, the engine heats up to a relatively high temperature. Radial thermal expansion is accommodated by expansion of the inner ring, causing the tabs to move deeper into the grooves. Longitudinal thermal expansion is accommodated by slippage of the tabs along the grooves in a longitudinal direction. Meanwhile, the engine is supported against bending and flexing beyond the amount permitted by the space between tab ends and bottoms of the grooves.

Abstract: An artificial space object capable of operating usefully adjacent to, but not in orbit about, a celestial body such as the Earth, comprising: payload means for providing useful services from a position in space adjacent to the Earth, light pressure propulsion means for intercepting light pressure and directing the resulting force to oppose the gravitational force between the Earth and the space object; and attachment means for attaching the propulsion system to the payload, whereby the force generated by the propulsion system may be transmitted to payload. The invention is designated a "Statite", i.e. a useful space payload maintained by light pressure in a position adjacent to the surface of a celestial body, but not in orbit around it. The propulsion system may be a solar sail or it may be a solar photon thruster. The useful payload may be the space segment of a communications, broadcasting, remote sensing, or any other useful space system.

Abstract: A pod for suspending a turbojet engine unit below the wing of an aircraft includes a suspension assembly with two laterally spaced front beams connecting the turbojet fan casing to the wing, and two rear links disposed in a common vertical plane and pivotally connected at one end to the wing and at the other end to a connection link which is connected at least to the exhaust casing of the engine, the front beams being interconnected by cross-bracing and being connected at the level of the downstream edge of the cross-bracing to at least one fixed part of the engine.

Abstract: The device is an alternative to the conventional paddle or oars, and comprises a collapsible scoop and a handle-shaft. The scoop has top and bottom panels 14,16, hinged together along one edge 18, and side-panels. The side-panels 20 are foldable, and allow the scoop to open and close. When the handle is pushed, the scoop opens out by the action of hydrodynamic forces; when pulled, the scoop collapses. The scoop is made from a one-piece blank cut from stiff plastic sheet. The hinges are formed by locally creasing the plastic material.

Abstract: A thrust reverser for jet engines comprising a pair of symmetrical thrust reverser door members which are pivotally mounted on an engine about an axis which is substantially diametrical with respect to the exhaust nozzle of the engine, the doors having scarfed trailing edges in order that they may pivot between stowed and deployed positions, a pair of pivotally mounted half-shells surrounding at least the trailing edges and defining a planar exhaust outlet for the engine; the pivot axes for the doors is movable in order to vary the area of the exhaust outlet defined by the half-shells depending upon the particular stage of flight.

Abstract: A door assembly is provided for an aircraft that has a fuselage with a protective skin and an access opening therein. The door assembly includes a pair of parallel tracks mounted on opposite sides of an access opening in the fuselage. A sliding door is secured to the tracks and is mounted thereon for reciprocal movement therealong. Some releasable restraining mechanism is provided for immobilizing the door relative to the tracks. A sliding aircraft door according to the invention allows openings of greater size to be employed in aircraft. Also, the system is far less complex, more economical to build, and lighter in weight then conventional aircraft door assemblies. The reduced weight results in greater fuel economy during flight, while the simplicity of construction reduces the likelihood of a malfunction in the door mechanism.

Abstract: A marine propulsion device comprising a transom bracket adapted to be mounted on a boat transom and including laterally spaced rearwardly extending port and starboard portions, and a swivel bracket including a first leg connected to the transom bracket for pivotal movement about a horizontal axis and a second leg extending generally perpendicularly to the first leg and including a transversely extending portion extending in closely adjacent relation to both of the rearwardly extending laterally spaced transom bracket portions and substantially bridging the space between the rearwardly projecting laterally spaced transom bracket portions.

Abstract: A track fastener apparatus for use with a locking track of the type used to secure a seat or cargo apparatus to the floor of an aircraft. The track includes a slot, and the upper walls of the slot have regularly spaced-apart enlarged openings separated by relatively narrower track slot segments defining locking segments. The track also includes a channel for carrying wiring along the length of the aircraft. The track fastener apparatus includes a housing. A screw member cooperates with the track fastener housing and the locking wedge to perform first and second functions in distinct first and second locking wedge positions. In the case of the first position the locking wedge is not completely positioned in alignment with and into the one enlarged opening, preventing the locking wedge from being tightened into the track. In the case of the second position the locking wedge is positioned in alignment with and into the enlarged opening, permitting the locking wedge to be tightened into the track.

Abstract: An auto-inflated life buoy has a belt-like air bag and an air container. The belt-like air bag defines a hollow bag, and has tongue secured on the inside wall of one end and a groove secured on the inside wall of the other end. The air container secured on the outside wall of one end of the belt-like air bag includes an air inlet, an internal chamber and an inlet nozzle. The air inlet coupled to the belt-like air bag is in open communication with the internal chamber which has a press button on the top and a film on the bottom. The lower part of the press button is combined with a pressure spring.

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).