Abstract: A deflated airbag is located on the outside of a missile or other vehicle beneath a folded, pivotally mounted airfoil member prior to launch, and a supply of pressurized gas is connected to the interior of the airbag via a suitable valve. After launch, or after lowering of a launch platform in the case of launch from an aircraft, an actuator such as an acceleration sensing device or timing device opens the valve, supplying gas to inflate the bag and simultaneously urge the airfoil into an extended, working position. After the airfoil is locked in its extended position, the airbag rapidly deflates and may be dropped off or retracted. Where more than one airfoil is to be deployed, separate airbags are located beneath each of the folded airfoils and a common gas supply is connected to all of the airbags.

Abstract: A cold vapor pressurization system for outer space vehicles that is used prior to and during engine burn to pressurize its fuel tank and oxidizer tank to produce the required engines net positive suction pressure (NPSP). The engine start system uses reaction control system (RCS) hydrazine to pass through a gas generator where it is disassociated. The by-products are then introduced into the hot side of the propellant heat exchangers. An oxidizer feed system and a fuel feed system pass through the respective cold sides of the heat exchangers to vaporize the propellants which are then used to produce the required engine NPSP for the oxidizer tank and fuel tank respectively. This system could also be used to provide engine NPSP during engine burn.

Abstract: An exhaust gas management system for missile launch arrangements which incorporates multiple launch cells exhausting into a common plenum. The system provides a flow passage configuration with a transition section that permits rocket exhaust flow gas to expand to fill the channel area downstream of the nozzle exit. Automatic aft closure members are included which serve to close off the flow passages to inactive cells while providing an open passage for exhaust gases from an active cell undergoing a missile firing. This arrangement prevents back flow or recirculation of exhaust gases into the volume in the cell which is upstream of the rocket nozzle exit.

Abstract: An airplane has a control device for providing a directional moment to control yaw during high angles of attack. The control device includes a chine support member carried at the forward end of the airplane forward of the fuselage. The chine support member rotates about a chine axis which is parallel or coaxial with the longitudinal axis of the airplane. A chine is mounted to the chine support member, the chine having a pair of substantially flat, thin, flight control surfaces rigidly mounted on opposite sides of the chine support member. These flight control surfaces rotate with the chine support member to control vortices formed on the chine during flight to provide directional moments. A drive motor will rotate the chine support member to control the angle of the chine. A control means including the aircraft computer controls the drive motor.

Abstract: The purpose integrated aerospike rocket engine and space vehicle aerobrake is to provide for optimum installation and performance of these systems in a space vehicle. By integrating the aerospike engine into the middle of the aerobrake, the engine can be located with its center of gravity toward the face of the aerobrake. This location permits the maximization of the displacement of the aerodynamic center of pressure of the aerobrake relative to the center of gravity of the space vehicle, thereby maximizing the stability of the vehicle upon aerodynamic capture at the earth or another planet. By substituting an aerospike rocket engine for a conventional bell nozzle engine, the doors required to close the aperture in the aerobrake to accommodate the conventional engines can be eliminated. In addition to the unique combination of the aero-spike engine and the aerobrake, an included unique feature of the invention is the extendable nozzle plug.

Abstract: An improved wind tunnel six component balance having an outer shell assembly that receives a tubular inner rod and an axial member that is received within the interior of the tubular inner rod. The forward and aft ends of the outer shell assembly are connected to the inner rod. The loads imposed on the forward and aft ends of the outer shell assembly are transferred to the inner rod and into the tunnel support system. The central annular section of the outer shell assembly is connected to the axial adapters (four each and into the central disk of the axial member. The principal areas of the axial element are the central disk member, the flexures (two sets forward and two sets aft), the forward and aft gauged sections, and the forward and aft disk members. Normal force, side force, and rolling moment are carried by the outer forward webs of the outer shell assembly. The axial member will transfer the majority of the axial force then the forward and aft outer shell webs.

Abstract: A filament wound composite structure, its tooling and method of manufacture. The isogrid filament wound composite structure is formed having at least one or more pseudo-isotropic laminate zones in its joint regions. This structure is realized through the use of specialized tooling. The ribs of the isogrid filament wound composite structure are discontinued by tapering them out into a thin skin. This is accomplished by gradually widening the grooves in the mandrel while simultaneously decreasing the depth of the grooves. This gradual change in the tooling redistributes the material in the ribs into a thin skin. The fibers that are redistributed into this thin layer, coupled with the skin wound over the top of the ribs, provide the necessary reinforcement in the joints.

Abstract: A method and arrangement for integrating a Global Positioning System and an Inertial Navigating System without the use of accelerometers to provided a velocity steering signal that is utilized in the guidance of a flying vehicle, such as a space craft. The method and arrangement do not require the use of accelerometers. A mechanization for interfacing the integrated Global Positioning System and the Inertial Navigating System with a flight control system which controls a flying vehicle is disclosed.

Abstract: An optical edge guidance system for automatic riveters. The guidance system utilizes a light source which directs light toward the material to be drilled/riveted, a video camera is also directed toward the portion of an object to be drilled/riveted and detects reflected source light from the material. The light from the source directed toward the material is angled about 10 to 15 degrees from the vertical. The material either is marked with a dark stripe or, for example, when the material cross-section is in the shape of a hat section, i.e. an aircraft longeron, a shadow is cast by the light striking the edge of the material and forms a dark area along the longitudinal centerline thereof. The edge of the dark stripe or shadow is detected by the video camera. The video signal from the camera is processed into a voltage equivalent of the video signal. A known reference voltage signal is established when the material positioned properly for drilling/riveting.

Abstract: Disclosed are formulations for producing chemical solvent admixtures that can be employed to clean a surface for further work; and that can be applied to cloths for the cleaning operation yet alleviate problems with solvent evaporation into the atmosphere to cause many legal and environmental problems, and a method of storing and disposing of cloths soaked with the formulation that alleviates current problems.

Abstract: A solar concentrator panel having an array of off axis cylindrical parabolic mirrors with an optical design of relatively short focal length solar cells arranged in line that converts sunlight to electricity. The back surface of the mirrors are used as the solar cell mount and the heat sink for the adjacent mirror.

Abstract: A magnetic gun for the purpose of accelerating a metal clad projectile to high velocities which includes a long dipole magnet extending the length of the gun bore that encloses a plurality of short superconducting dipoles magnets along its length. The short dipoles are superconducting dipoles whose induced current and magnetic field oppose the current and magnetic field of the long dipole. The short dipoles while in a superconducting state prevent the long dipole field from entering the gun bore. When the short dipoles become normal conducting, the current in the short dipoles decay rapidly. When this occurs the field of each of the small dipoles collapse and magnetic flux from the long dipole enters the gun bore at the locaiton of the normal conducting small dipole. This entering flux repels the projectile down the barrel in the direction of least flux, so the projectile is moved to the next short dipole section.

Abstract: A method is presented for the accurate quantitative determination of amounts of reactive (water and ethanol) and non-reactive N-methyl-2-pyrrolidone (NMP) volatiles in graphite-polyimide prepreg samples. The method is also applicable to other condensation-curing and/or solvent-impregnated prepreg systems, regardless of the type of reinforcement. Prepreg samples are heated in a containment chamber and the volatiles are subsequently flushed from the chamber with dry nitrogen gas. The volatiles are condensed, weighed, and analyzed via gas chromatography to determine the volatile composition. The method offers a means of purging the extremely tightly held, relatively non-volatile NMP solvent from the resin matrix by means of high temperatures applied to the sample chamber. The higher volatility reaction products are also captured by means of the specially designed very low temperature condenser. An internal check (collection efficiency) on the accuracy of the results is included in the test method.

Abstract: A structural arrangement is provided in conjunction with the upper closure of a missile cell which, upon launch of the missile, generates a rarefaction wave which assists in closing the bottom closure of the missile cell. As a result, reverse flow of exhaust gases back up into the missile chamber from an associated plenum chamber is prevented or minimized.

Abstract: A cascaded magnetron device has an elongate cathode shank extending along its axis and a series of tubular anode elements placed end to end in a linear cascade surrounding the cathode shank along at least part of its length. Each adjacent pair of anode elements is separated by a conductive, annular pin down disc, and the cathode shank has a series of spaced bands of field emitting material separated by non-emitting regions, each band being located within a respective one of the anode elements and spaced inwardly from the ends of that element. Suitable power inputs and magnetic field generators are provided for generating electron emission and oscillation in the interaction zone between each emitting band and the anode element surrounding that band, and suitable extraction devices are provided for extracting power from each of the interaction zones, the arrangement producing phase-locking of the cascaded magnetron bodies.

Abstract: A relativistic magnetron device comprising an elongate cathode shank extending along the axis of the device and a cylindrical anode surrounding the cathode shank along at least part of its length to define an annular interaction area. The anode has an even number of resonator cavities facing the cathode, and microwave extraction devices are connected to alternate resonator cavities to extract power from the device. The cathode has a central, emission band extending from the center of the interaction area in opposite directions and terminating short of the ends of the anode, while the remainder of the cathode is non-emitting.

Abstract: A method for injecting a chemical barrier into a surface aperture is provided. The method provides a vacuum to a work site to evacuate the air from the work site. Then, an injector head is located and retained at the work site. The injector head has a gasket that forms a seal around the work site. Pressurized fluid is conveyed to the work site through a first conduit in the injector head. Any unused fluid is conveyed away from the work site by a second conduit in the injector head.

Abstract: An air liquefier and separator of air constituents for a liquid air engine. Its unique structure captures the ambient air and guides it through guide vanes into a bank of spiral tubes or channels where the air is completely contained while being liquified and separated into its constituents. The spiral tubes or channels provide a compact heat exchanger design with long tube length or channel length for efficient heat transfer and liquefying of the air which is accomplished by a flow of liquid hydrogen flowing either inside a concentric tube inside the air condensing tube or flowing in a tube or channel with a common wall in contact with the air condensing tube or channel. The liquefier can easily be designed to be an integral part of a liquid air jet engine installation.

Abstract: A self-contained alcohol purging and cleaning system for direct writing type trace recorders utilizes a source of compressed air, a tank of R-22 refrigerant and a tank of isopropyl alcohol. A main supply line tube may have its inlet port end selectively connected to either the source of the compressed air or the R-22 tank. The outlet port end of the main supply line tube is connected to the inlet port of the alcohol tank. A first elongated tubing member has its one end connected to the outlet port of the alcohol tank and its free output port end may be detachably connected to inlet end of an output hose whose outlet end is detachably connected to the ink supply manifold of a direct writing type trace recorder. By opening various valves of the system, pressurized gas passing through the main supply line tube forces the isopropyl alcohol into the ink supply manifold and out through its outlet ports until thickened ink is purged and the isopropyl alcohol flowing therefrom is reasonably clear.

Abstract: A high strength synthetic resin based structural material in which a polymer having coil-like molecules is uniformly mixed with a second polymer having rigid rod-like molecules. This material is made, basically, by dissolving a thermoplastic matrix polymer having coil-like molecules in a suitable solvent, adding thereto thermosetting polymer reactants which then form a prepolymer. The rigid rod prepolymer may then be partially cyclized through heat or by the use of a chemical agent in order to reduce chain conformations. Excess cyclizing agent can then be removed and the mixture can be heated to complete polymerization to produce a high strength structure with rigid rod-like molecules intimately blended with the matrix coil-like molecules.