Abstract: A parachute system for an airman ejected from an aircraft in an ejection seat includes at least one drouge parachute housed within a rigid hollow container. In conventional manner, the drogue parachute is connected by lines with releasable attachments on the seat, one of the lines being further connected with the main parachute so that the latter will be deployed after release of said attachments. The container is formed as a projectile mounted in a gun mounted on the ejection seat. The container has, at its end facing away from the direction in which it is fired, a closure connected with the lines and with the drogue parachute. When the container and closure are fired from the gun, and the closure is arrested abruptly by the lines, the container continues in its trajectory whilst the drogue parachute is drawn from the container and deployed by the lines.

Abstract: A propulsion unit suspension for propeller driven aircrafts in which a supporting frame is supported at a fire wall; the propulsion unit together with auxiliary aggregates is retained at the supporting frame in several bearings. The bearings of the supporting frame are arranged in two horizontal planes offset in height to one another with an axial distance to one another. The arrangement of the bearings takes place in such a manner that a line of action of the gravity and a further line of action of the propeller thrust extend through an ideal surface delimited by the bearings. In particular, the forward bearing is retained at the supporting frame within the area of a vertical longitudinal plane through the center of gravity as well as above the line of action of the propeller thrust and two rear bearings are located in the supporting framework at approximately the same distance on both sides to the vertical longitudinal plane of the center of gravity and below the line of action of the propeller thrust.

Abstract: A structural external insulation for hypersonic missiles which reach speeds hat cause surface temperatures on the cylindrical shell structure to reach up to 3000.degree. F. for a period of time. The invention incorporates efficient high temperature insulation as an integral part of the composite shell manufacturing process (tape layup and/or filament winding).

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: A toy parachute is disclosed for attachment to a kite string and for after travelling up the string and contacting stop means being released from the string for free flight to the ground. The toy includes a carrier which is slidable up and down the kite string coaxially disposed thereabout. The parachute is releasably coupled to the carrier by a novel split sleeve member having a central aperature into which the upper end of the carrier may be inserted. The split sleeve member has a major slot throughout its length which permits the kite string to pass therethrough on uncoupling of the split sleeve from the carrier so as to release the parachute toy from the kite string.

Abstract: An externally mounted fire or explosion suppressing device for aircraft f tanks includes a bottle of pressurized fluid suppressant agent, the bottle having a primary duct ending in a seal disposed against the exterior surface of a tank wall. A secondary duct is disposed at an angle to the primary duct and carries a pyrotechnic charge that is detonated in response to an optically detected flash in the tank and explosively cuts through the seal and tank wall to release suppressant into the tank.

Abstract: A mounting and mounting method for a sensor positioned within a tubular axle of an aircraft undercarriage which will provide an output voltage proportional to the angular deflection of an axle for computation of aircraft gross weight. The sensor is not affected by cross-sectional distortions of the tubular axle under loading, undersirable shear frictional effects at the interface between the sensor mounting and the tubular axle and differential angular deflections of the axle.The cylindrical mounting member for the sensor has a pair of O-rings adjacent opposite ends thereof which are positioned to space the periphery of the mounting member from the bore of the tubular axle and which are under radial compression and act to provide uniform radial compressive forces applied about the full circumferential periphery of the cylindrical mounting member and absorb distortions of the axle by elastic deformation thereof.

Abstract: The invention relates to a parachute including a steerable canopy. Steerability is achieved by providing a venting gore in the canopy and two or more maneuvering suspension lines secured to the hem of the canopy on opposite sides of the venting gore. The maneuvering suspension lines are arranged to be extendible so that on extension it allows the canopy hem in the region of the gore to lift slightly to provide a forward drive to the canopy in flight. During flight the canopy may be steered by manipulation of the maneuvering lines thereby to change the direction in which air escapes from the canopy. The canopy may also be fitted with an auxiliary suspension system arranged and adapted to reduce opening time of the canopy.

Abstract: An apparatus for transporting a spacecraft and fluid propellant from the earth to a substantially low gravity environment above the earth with substantially reduced loading of the spacecraft due to forces upon the fluid propellant during the transport, the apparatus including a vehicle for carrying the spacecraft and the fluid propellant from the earth to a substantially low gravity environment above the earth; a plurality of external tanks disposed within the vehicle, external to the spacecraft, for containing the fluid propellant as the vehicle carries the spacecraft and the fluid propellant from the earth to the substantially low gravity environment above the earth; a plurality of spacecraft tanks disposed within the spacecraft for receiving the fluid propellant and for containing the fluid propellant; and means for transferring the fluid propellant from the external tanks the spacecraft tanks in the substantially low gravity environment above the earth.

Abstract: Inflatable or pneumatic float assembly has tough outer fabric tubular shell with an upper wall having a first elongated sleeve extending therealong to receive an elongated stiffening member. A lower wall of the float is stiffener by stiffeners to provide a step having an essentially upright transversely extending step wall. The float has a plurality of internal baffles which form inflatable compartments within the float, preferable to receive air filled bladders. The elongated stiffening member extending through the first sleeve has exposed portions to provide access for attachment means which cooperate with the exposed portions to permit the stiffening member to cooperate with an aircraft undercarriage. Wheels can be provided to permit the aircraft to be amphibious for landing on land as well as water, with various structures to permit changing relative positions of the wheels and the floats.

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 system for circulating heated gases within the circular leading edge of a jet engine housing to prevent ice build-up thereon, or to remove accumulated ice thereform. Hot gases such as air from a hot, high pressure section of the jet-engine are directed through a conduit. The conduit enters the annular leading edge housing, usually from the aft side through a bulkhead, then turns about 90.degree. to a direction tangential to the leading edge annulus. The hot gases exiting the tube entrain the cooler air in the housing, causing a much larger mass of air to swirl circularly around the annular housing. The entering hot gasses heat the mass of air to an intermediate, but still relatively hot, temperature. This large mass of circularly moving hot air is quite efficient in uniformly transferring heat to the skin of the leading edge without leaving any relatively cold areas and preventing the formation of ice thereon.

Abstract: Each suspension line of a multi-cell gliding parachute is connected through a lower loop of a primary reinforcing tape folded over on itself. The upper overlying segments of the primary reinforcing tape extend partially across and are stitched to one side of a corresponding fabric rib connected between upper and lower fabric canopies of the parachute. The upper ends of the segments terminate below the upper canopy and are connected to a secondary reinforcing tape also stitched to the rib and spaced from the upper canopy. The upper segments of the primary reinforcing tape and the secondary reinforcing tape form a Y, T or other configuration serving to distribute the load from the suspension line without puckering or otherwise altering the preferred airfoil configuration of the upper and lower canopies.

Abstract: An aircraft automatic trim system is operable during autopilot control to transfer trim from the elevators to the stabilizers. The thresholds for trim transfer are based on the ratio of elevator demand to available elevator control. Trim commands are produced responsive to this ratio exceeding an amplitude and time dependent limit.

Abstract: An inflatable evacuation device to simultaneously evacuate from both an overwing aircraft exit and an aircraft exit aft of the trailing edge of the aircraft wing.

Abstract: A control force generator for an aircraft using circulation control to a selectively produce lift on an otherwise non-lift surface. The generator employs a novel, double-slot single Coanda surface arrangement for selectively generating the aerodynamic lift.

Abstract: The invention relates to a preloadable vector-sensitive latch which automatically releases when the force vector from a latch member reaches a specified release angle. In addition, it contains means to remove clearance between the latched members and to preload the latch to prevent separation at angles less than the specified release angle. The latch comprises a triangular main link (77), a free link (74) connected between a first corner of the main link and a yoke member (72), a housing (82), and an actuator (71) connected between the yoke member and the housing. A return spring bias means (70) connects the main link to a portion of the housing. A second corner of the main link is slidably and pivotally connected to the housing via a slot (81) in a web portion of the housing. The latch housing has a rigid docking ring (79) alignable with a mating locking ring (75) which is engageable by a locking roller (78) journalled on the third corner of the triangular main link.

Abstract: Apparatus for use in gyroscopically ejecting a spacecraft supported in the open end of a spacecraft supporting cradle. The invention comprises a separable ejection restraint mechanism attached between the cradle and the spacecraft. The mechanism restrains the thrust force applied to the spacecraft for a predetermined time period in order to dissipate undetermined forces acting upon the spacecraft prior to the ejection thereof. The mechanism comprises a separable resilient portion and a releasable clamp portion coupled thereto. The resilient portion comprises a spring loaded anchor rod arrangement while the releasable clamp portion comprises a spring loaded split ball clamp arrangement. The invention also contemplates the use of a flexible carrier coupled between the spacecraft and the cradle. The invention acts as a tether connected between the cradle and spacecraft which acts to establish a determinant state of force on the cargo and eliminate unwanted ejection-related problems prior to cargo deployment.

Abstract: Deployment mechanism for a ram air turbine has conventionally consisted of a strut pivotally mounted within a storage bay of an aircraft and which pivots to a downwardly-extending position to bring the ram air turbine into deployed position. Such a structure has required a storage bay in the aircraft having a large stowing volume because of the primarily rotational movement of the ram air turbine and has not maximized the speed of deployment of the ram air turbine. The improved deployment mechanism for the ram air turbine has front and rear linkages pivotally connected at one of their ends within the storage bay of the aircraft and their other ends pivotally connected to the ram air turbine and includes a spring-loaded deployment actuator operable to move the ram air turbine from stowed position.

Abstract: Portable aircraft arresting apparatus is disclosed which is comprised of a towable wheeled trailer providing a frame adapted to be anchored along a runway or landing strip and which is adapted to selectively support two different energy absorbing units, one of which includes a tape reel rotatable about a horizontal axis and the other of which includes a tape reel rotatable about a vertical axis. At least partially different tape patterns and paths are required with respect to the tapes on the two reels, and the frame carries sheave components which provide the required tape patterns and paths for the tapes on the two reels. In accordance with another aspect of the invention, the sheave components provide selectable tape issue paths, one of which opens laterally of the frame and the other of which opens longitudinally of the frame, thus providing selectivity with respect to positioning of the apparatus relative to a runway.