Abstract: An elongate helicopter body including an orthogonally mounted rotatable and pivotally positionable rotor shaft fixedly mounting a solid, annular, convex blade member defined by a parabolic convex curve and terminating in an annular rim, wherein the rim is aligned generally orthogonal to the rotor shaft. Propulsion is provided by an enclosed CO2 cartridge, or alternatively a propulsion propeller in alignment with the body of the helicopter. Modifications of the instant invention include a lift propeller mounted underlying or overlying the solid blade and is of a generally equal diameter to that defined by the blade.

Abstract: Asymmetrical mechanical linkages for sidestick roll controllers located at the pilot and copilot stations of aircraft and other vehicles with fly-by-wire control systems. The asymmetrical character of the linkage reduces the level of exertion required to rotatably displace the sidestick in the outboard direction and, as an important consequence, significantly reduces pilot fatigue.

Abstract: A dual eccentric bearing system for precise adjustment of wing incidence and dihedral. The bearing system is utilized in the attachment of wings that vary the sweep by rotation about a pivot fixedly located on an aircraft fuselage through an interconnecting wing pivot pin. The top portion of the pivot pin is supported by the dual eccentric bearing system and the bottom by a non-eccentric bearing system. The eccentric bearing system has both an eccentric ball retaining ring free to rotate relative to its fuselage attachment and a ball contained within the ring which includes an eccentric pivot pin receiving aperture free to rotate within the ring containment. The bottom end of the pin is supported by a conventional non-eccentric bearing system with the ring fixedly held in position by its fuselage connection. The ball of the non-eccentric bearing has a similar pin receiving aperture with the ball free to rotate angularly relative to the ring.

Abstract: A powered canopy breaker attached to an ejection seat, that fractures a canopy when the seat is ejected. The breaker has a piston that is operatively connected to an explosive cartridge. When the seat is ejected, the piston engages the canopy, pushing the piston a predetermined distance until the cartridge is detonated. The detonated cartridge ignites a detonating cord that fractures the canopy.

Abstract: An apparatus for both de-icing and anti-icing an aircraft in one "pass". A pair of units are positioned above and below the aircraft. Each unit has respective nozzles oriented in one direction for dispensing de-icing fluid/air onto the aircraft as it approaches the units. Each unit further has respective nozzles oriented in an opposite direction for dispensing anti-icing fluid/air onto the aircraft as the aircraft moves away from the units. The apparatus is bi-directional so that the aircraft may approach the apparatus from either of two opposite directions. Means are provided for collecting and recycling the run-off of the de-icing and anti-icing fluids, respectively.

Abstract: A structural member having integral surface de-icing capability and method of manufacture are described. The structural member includes a non-metallic high tensile modulus fiber-reinforced matrix structural backing, thin force and displacement generation means, and a thin high tensile modulus outer skin bonded to said backing and said force and displacement generation means which is positioned between the backing and the skin. The force and displacement generation means may include one or more inflatable tubular members and/or electromagnetic apparatus. The structural member may be substituted for the aluminum alloy leading edge structural skin typically employed on modern aircraft.

Abstract: A fire sprinkler apparatus comprises a tubular body, a valve and a locking mechanism, the tubular body having a longitudinal axis and a conduit extending therethrough and being connectable to a supply of pressurized fire extinguishing fluid. The conduit has an annular groove proximate the outlet end of the tubular body, the valve forming a fluid-tight seal proximate the outlet end in a closed position and being completely separable from the fire sprinkler apparatus. The locking mechanism being supported by the tubular body for limited movement between an engaged position and a disengaged position, the locking mechanism comprising a housing, a plurality of locking balls moveable toward and away from the annular groove, a locking disc and temperature responsive means.

Abstract: A modular space structure having a central enclosed area is erected in outer space from expandable modules transported by a reusable space shuttle or an expendable rocket. Each module comprises an outer member and one or more inner members carried telescopically therein forming a complete enclosure to serve as a small self contained space structure capable of being equipped for life support. Each inner member has slightly less volume than the outer member in which it is nested. As each inner member is extended, the interior volume is increased and a larger enclosure is formed. A two member module, when extended, would nearly double the amount of initial enclosed usable space, and an extended three member module would nearly triple the amount of initial enclosed usable space.

Abstract: A reeling control system and an air driven tow reel machine incorporating such a control system are disclosed. In the disclosed control system and reeling machine of the present invention, towline velocity is monitored and reel-in and reel-out operations are regulated according to a programmed towline velocity profile. A position sensor senses the position of the turbine vent doors and a velocity sensor device provides the instantaneous towline velocity. A velocity comparator compares the instantaneous towline velocity with a desired velocity value from a desired velocity profile. Based upon the difference between actual and desired towline velocities, a door control device generates a driving signal for controlling the vent door position accordingly.

Abstract: The present invention is a balloon system for transporting a load wherein an aerostat is movable, both horizontally and vertically, throughout a working area defined by the guy lines that anchor the aerostat. Such area can include multiple pickup and discharge points. The balloon system is especially useful for logging in inaccessible or rugged terrain and transporting heavy loads between widely separated pickup and discharge points with intervening obstructions rendering group transport difficult. Individual loads may be picked up at any point within the working area for movement to a discharge point for unloading, after which conventional load handling equipment may be used to handle the load. A plurality of at least three guy lines radiating downwardly from the aerostat anchors the balloon to individual and separately controllable ground-based guy line control and storage apparatus. Each control apparatus is controllable to extend or retract its respective guy line.

Abstract: A solid material, such as sand, mineral tailings, aggregate, or sludge is selected and treated to wet the surface of the material. A low moisture content foam is generated by passing a gas through a mixture of water and a surfactant, wherein the foam has a foam weight in the range from 15-50 gm/l. The solid material then is mixed with a quantity of the foam from 2-80% by resulting volume, sufficient to create of a foam-based slurry product having plug flow characteristics when pumped through a pipeline. The mixing can be accomplished by batch process or continuous flow processes. The slurry product is pumped through a pipeline and is regenerated as required within the pipeline by injecting additional foam into the slurry product while, substantially at the same time, mixing the slurry product with the additional foam by passing it over a mixing foil, which is especially effective in a bend of the pipe.

Abstract: A breather outlet for the gearbox of an aircraft mounted gas turbine engine comprises an aerodynamic mast which extends from the engine nacelle. The mast contains a breather duct which interconnects the interior of the gearbox with an exhaust outlet. The exhaust outlet is generally rearwardly facing and is spaced apart from the engine nacelle so as to avoid oil staining of the nacelle.

Abstract: An oxygen supply system for use in an aircraft has four check valves (19) each having an inlet connected to a source of oxygen, and an outlet connected by a flexible hose (17) to a face mask (13). The check valve (19) associated with each face mask has a detachable pin (26) forming part of a collar (27) which embraces the hose (17) and is tethered to a looped section (29) of the hose. When the pin is detached from the check valve, by pulling the face mask down, oxygen is supplied to the mask.

Abstract: A powered canopy breaker attached to an ejection seat, that fractures a canopy when the seat is ejected. The breaker has a piston that is operatively connected to an explosive cartridge. When the seat is ejected, the piston engages the canopy, pushing the piston a predetermined distance until the cartridge is detonated. The detonated cartridge thrusts the piston back, fracturing the canopy.

Abstract: An aircraft cowling (20) is comprised of a cowling body (22), forward and aft bearings (24,25) disposed on the cowling body (22), corresponding sets of guides (29,30) disposed on and conforming with the shape of the aircraft (26), a screw fastener assembly (74), latches (82), and complementary interaction between the cowling edges (68,70) and aircraft edges (69,71) to provide lateral support for the cowling (20). The aft bearing (25) is comprised of two rollers (44) and two roller supports (46) which are disposed on the cowling body (22) in a manner permitting lateral motion and coupled by a shaft (50) with right-hand threads (56) on one end and left-hand threads (58) on the other end. The shaft (50), due to the opposing threads (56,58), restricts the roller supports (46) to convergent and divergent movements and prevents movement in a common direction, thereby providing lateral support to the cowling (20) during opening and closing.

Abstract: An airship having improved controllability which comprises: an axial fluid pathway penetrating through a body of the airship in an axial direction, at least one radial fluid pathway crossing the axial fluid pathway and penetrating through the body in a radial direction, the axial fluid pathway and the radial fluid pathway forming a ventilating-thrusting tube having a rigid framework construction, propulsion means, thrust generating direction of which is adjustable, arranged in a crossing region of the axial fluid pathway and the radial fluid pathway, and a lift balloon arranged beside the ventilating-thrusting tube in such a manner that a gap is formed between the ventilating-thrusting tube and the lift balloon to allow air to flow through. This arrangement lowers a tendency of yawing due to a transverse wind. The airship has a semi-rigid and semi-flexible construction capable of making up for drawbacks of both rigid type and flexible type.

Abstract: A door latching and lifting mechanism for use on an aircraft as an escape hatch. The door (10) is an upwardly opening plug-type door. Its latching mechanism (12) consists of a torque tube (80) and handle (90), both of which are carried by the door (10). Pulling on the handle (90) rotates the tube (80) and causes door latch pins (113) to retract, thus releasing the door (10). A preloaded lift spring (48), connected to the door (10) by an overhead cable (18), automatically pulls the door upwardly as soon as the pins (113) retract.

Abstract: Control apparatus, such as an aircraft throttle box, includes a manual control member 8 linearly movable on a first shaft 2. The position of the control member is sensed by rotation of the shaft 2 to generate an output control signal. In order to balance the apparatus, especially against high g-forces, a second shaft 3 is provided, parallel to the first carrying a counterweight 13 that moves together with the control member 8, but in the opposite direction.

Abstract: A crew protection system designed to isolate an aircraft crew and provide a means for safely evacuating an aircraft, particularly hypersonic vehicles, in emergency situations. The crew compartment is designed within the forebody of the main vehicle. The forebody is designed so as to separate cleanly from the main vehicle as by generation of a circumferential structural break, in the event of a catastrophic failure or explosion of the main vehicle fuel tank. In the event of such an uncommanded failure of the main tank and propellant combustion, resulting in the above noted structural failure, the resultant pressure impulse thrusts the forebody containing the crew compartment clear from the remainder of the vehicle. The provision of a system of baffles in the forebody between the crew compartment and the fuel tank, and the shape of the forebody and the materials used in its construction mitigate the effects of the blast pressure impulse on the crew.

Abstract: A kite apparatus which may be attached to the center spar of a stunt kite which allows the common string of the two yokes to pass through a pulley and when one of the kite control strings is pulled, the common string rides over the pulley causing un-equal lengths of the common string on each side of the pulley, thus changing the attack of the surface of the kite to the wind which provides a new and unusual control resulting in better maneuverability.