Abstract: A high lift vertical takeoff and landing aircraft has first and second fuselages connected by a central airfoil. Jet engines at the leading edge of the airfoil expel propulsive streams simultaneously over top and bottom surfaces of the foil. Extendable flaps are utilized at a trailing edge of the airfoil with a horizontal control blade being attached to the leading edge of the foil. The control blade is within the jet's propulsive stream to permit proportioning of the stream above and below the airfoil.An extendable augmenter wing is attached between the fuselages aft and above the main airfoil to permit airflow in this region to be directed downwardly, accelerating the flow and providing additional lift.The main airfoil is positioned so that the fuselage walls extend above and below the foil. Lateral flow of the main engine exhaust is restrained by these walls. Above the wing the walls and airfoil create a venturi to speed airflow and decrease pressure.

Abstract: A reusable landing zone transportable as equipment in an emergency vehicle and rapidly deployable by persons on the ground is disclosed for marking an area where a helicopter may safely land on an suitable surface. A plurality of bar masses are removably disposed on top of and attached near the edges of a rectangular foldable sheet using spring-closed hooks. Similarly, a bag mass is removably disposed on top of and attached near each corner of the sheet. A foldable, highly visible and reflective target is attached to the upper surface of the sheet so that the center and size of the sheet may be easily seen.

Abstract: A high-performance aircraft seat is disclosed that automatically reacts to ecline the pilot as the aircraft experience higher G's in the vertical direction, or along the pilot's Z-axis. The seat, consisting of a seat pan joined to a seat back, is hingedly fixed, at a point forward of the pilot/seat combination center of gravity, to the surface. An hydraulic cylinder is fixed between the surface, aft of the hinge point, and the seat back and will react to return the seat to its initial position, from a "G-force" induced reclining position, whenever the "G" forces subside.

Abstract: A model airplane is provided wherein the fuselage formed with a tail is horizontally divided and provided at said aft end portion with a vertical stabilizing surface and two horizontal stabilizing surfaces. It is desirable that the aft end portion of the fuselage should be held together and a root or roots of the stabilizing surfaces be located with a smooth and streamlined surface being maintained on the underside of the aft end of the fuselage by insertion from the aft end of the fuselage. This is achieved in that a duct which is open at the aft end of the fuselage extends through the fuselage portions and portions of at least one root of a stablizing surface, and in that a pin is fittingly inserted in the duct. This method of connecting eliminates the need for screws, detents and a well in the underside of the aft end region of the fuselage.

Abstract: A navigable flat kite is described which has a linkage comprising cross bars and longitudinal bars, a sail mounted to the linkage and a balance mounted to the sail and/or the linkage and adapted to be connected with at least one navigation line. The kite consists of at least two individual kites which are connected by means of their cross bars such that the individual kites are adapted to be turned relative to one another around the cross bars as axis of rotation. The two individual kites have a sail surface with identical dimensions. Each individual kite is associated with at least one balance including at least one balance line which is mounted to the sail and/or the longitudinal bars above or below the cross bars.

Abstract: In an aircraft having a cylindrical or tapered pressurized fuselage, an internal bulkhead includes a central calotte shaped part of particular thickness and made of a fiber-mesh, a woven or a fleece-like reinforcement of a particular radius of curvature and preferably made of Kevlar: a possibly thicker edged portion of, preferably, carbon fiber-reinforced material, which possibly matches any taper of the fuselage, and a transition from the calotte shaped part to the edge having a radius of curvature smaller than the particular radius of the calotte shaped partition.

Abstract: A spacecraft attitude control system uses at least four reaction wheels. In order to minimize reaction wheel speed and therefore power, a wheel speed management system is provided. The management system monitors the wheel speeds and generates a wheel speed error vector. The error vector is integrated, and the error vector and its integral are combined to form a correction vector. The correction vector is summed with the attitude control torque command signals for driving the reaction wheels.

Abstract: A thrust reverser assembly is disclosed for a wing mounted gas turbine engine exhaust nozzle having a fixed outlet for discharging exhaust gases over a surface of the wing. The assembly in accordance with a preferred embodiment includes a deflector having forward and aft ends, and first and second sides joined together by a base. The deflector is positionable in a stowed position around the exhaust nozzle so that the aft end is disposed forward of the nozzle outlet for allowing substantially unobstructed discharge of exhaust gases therefrom, and in a deployed position for changing direction of exhaust gases for thrust reversal. Two pairs of first and second bellcranks are positioned adjacent to respective ones of the deflector sides and means are provided for rotating the bellcranks for moving the deflector between the stowed and deployed positions.

Abstract: A vertical take-off and landing aircraft is configured so as to provide, when landing tail-first with its fuselage (1) in a generally vertical attitude, a touchdown area (21) at the tail of the aircraft at a position offset from a line extending along the length of the fuselage through the centre of gravity (23) of the aircraft such that after the touchdown area contacts a landing surface the aircraft topples under the action of gravity to bring an undercarriage (11, 13) of the aircraft into contact with the landing surface, thereby to attain a stable landed position.

Abstract: The invention is a rotatable, non-circular forebody flow controller. The apparatus comprises a small geometric device located at a nose of a forebody of an aircraft or missile. The geometric device has a circular base that fits flush upon the remaining forebody of the aircraft and a non-circular cross-sectional area that extends toward the apex of the aircraft. The device is symmetrical about a reference plane and preferably attaches to an axle which in turn attaches to a rotating motor. The motor rotates the device about an axis of rotation. Preferably, a control unit connected to an aircraft flight control computer signals to the rotating motor the proper rotational positioning of the geometric device.

Abstract: An airlock for the batch or continuous feeding of a material while obstructing the free flow of a gas. The airlock comprises a continuous belt having a substantially horizontal upper surface and a plurality of non-porous flights projecting out from the belt. Each flight has a free edge located outwardly from the belt. The free edges of the flights seal against a planar sealing surface located above and parallel to the belt. Particulates are transported on the upper surface of belt below and away from any potential grinding action between the moving free edges of the flights and the stationary sealing surface. The flights, located between the sealing surface and the belt, inhibit the flow of air through the airlock.

Abstract: A gripping and locking arrangement for an aircraft movable component such as a flap door or undercarriage comprises a piston and a piston rod operative as a means for sensing a closing movement of the flap door or undercarriage, and also operative automatically actively to pull same by means of a closing hook into a position in which it is to be locked. The arrangement includes a locking member displaceable within the piston to move lock elements into a locking position and to hold them in the locking position until the arrangement receives a hydraulic pressure signal for causing lowering of the flap door or undercarriage, and the locking member is then displaced whereby the lock elements move into a release position. The hydraulic oil pressure can then act on the piston to produce displacement thereof into a position in which the closing hook releases the flap door or undercarriage component.

Abstract: A payload interface ring adapted to releasably secure a payload to a multiple payload adapter arranged to be carried into outer space by a launch vehicle for positioning of the payload in a suitable orbit relative to the earth. The interface ring includes a latching mechanism secured to a base to receive a berthing pin carried by the payload and to releasably latch the berthing pin for securing of the payload for transport of the payload to a desired orbit. A plurality of springs cooperate with the berthing pins and the latching mechamism to secure the payload in a desired latched position during transport to the desired orbit.

Abstract: A retractable landing gear is arranged so as to provide, in use, a highly inclined shock absorber while avoiding high shearing stresses on the shock absorber. The landing gear includes a pivoting panel fixed to an aircraft structure to pivot about a raising axis; a shock absorber including a strut fixed to the pivoting panel so as to pivot relative thereto about a tilt axis, and a sliding rod mounted to slide in the strut and carrying a set of wheels at its bottom end; and a coupling member connected to the pivoting plate and to the bottom end of the sliding rod. Also included is a mechanism for raising and holding the landing gear.

Abstract: The invention is a carrier for use in air dropping cargo from an aircraft, the carrier comprising a pallet suspended from a parachute. The pallet has struts which absorb shock and prevent cargo roll over when the pallet lands, the struts being deployed into a shock absorbing, anti-roll-over position by the drag of the parachute when it opens. The pallet includes shock absorbing supports between its upper and lower surfaces to further protect air dropped cargo upon landing.

Abstract: A locking arrangement for unfoldable solar generators which consist of several panels provides a lockable, partially-unfolded, intermediate position and a lockable, completely unfolded final position. In the partially-unfolded position, a panel is pivoted by 90.degree. so that a lock pin which is acted upon by a radially inwardly directed spring force and which, at first, slides on an outer section of a curve of a guiding contour, locks into an opening of a curved slot in a guiding element having the guiding contour. During the transition into the fully unfolded position, a plate cam, which had stopped at first, is rotated so that its driving groove can accommodate the lock pin which can now continue to slide on an inner section of the curve into the final locking position.

Abstract: A container fire nozzle hole adapter is provided for a wall structure having an opening. The adapter consists of a male component having a central aperture and a female component having a central hole therethrough sized to slip over the male component when the male component extends into the opening in the wall structure. The female component is mounted onto the male component within the container against the wall structure so that the adapter will be secured to the wall structure. A fire nozzle can be inserted into the central aperture of the male component for extinguishing a fire within the container.

Abstract: A low-cost square-shaped parachute has trapezoidal panels attached to its nopy sides for controlling the air flow during operation to maximize drag and stability.

Abstract: A movable cowling for an aircraft is disclosed having a stationary fairing portion attached to an engine support pylon and a movable cowling portion. The movable cowling portion defines a generally longitudinally extending slot to accommodate the stationary fairing portion when the movable cowling portion is in its closed position to enclose the aircraft engine. The movable cowling portion, which may be generally annular in shape and have a generally "C"-shaped cross sectional shape, is attached to the engine by way of a telescoping beam. A portion of the beam is attached to the movable cowling and a second portion of the beam is attached to the engine. The movable cowling moves in a direction generally parallel to the longitudinal axis of the engine such that it has no portions requiring lifting about a hinge axis. A locking mechanism is provided between the movable cowling portion and the stationary fairing to lock the movable cowling portion in its closed position.

Abstract: A fire extinguishing system for a Christmas tree including a base defining a water reservoir and having a submersible pump and container holding a fire extinguishing foam material mounted in the reservoir. A venturi block mixes the fire extinguishing foam material with water pumped from the reservoir upon detection of a fire condition by sensors scattered throughout the tree which mixture is discharged through a spray head mounted at the top of the tree. A relay connected to the fire sensors simultaneously closes an electric circuit to the pump and opens an electric circuit to the Christmas tree lights when the fire condition is sensed.