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 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: 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: 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: 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: 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.

Abstract: An improved break-away, end-of-arm robotic tooling assembly that has been designed to prevent damage to the robot arm in the event it would come in contact with something it should not. The robotic tooling assembly has a two inch inside diameter bore for air and paint lines. The robotic tooling assembly is compliant in all directions with the exception of a pulling force and it can be reset on repeating registration structure within the robotic tooling assemble. An air switch is incorporated which instantly signals the robot controller to perform an emergency stop.

Abstract: A deployable/retractable photovoltaic concentrator solar array assembly for space applications that includes a plurality of solar array panels that are carried by a pantograph arm arrangement that is deployable to position the panels in a predetermined canted arrangement for receipt of solar radiation. Each panel includes a plurality of spaced cylindrical off axis parabolic mirrors that concentrate the reflected light on a line that falls upon a series of photovoltaic cells arranged longitudinally along the back of each mirror. The cylindrical parabolic mirrors are aligned with the cylindrical axis perpendicular to the axis about which the panels are canted, so that such canting causes no loss of focus. The array panels may be hardened to resist perceived threats and the pantograph arm arrangement is operable to position the array panels in a preferred orientation according to the nature of the threat.

Abstract: A fuel system for horizontal takeoff and hypersonic aerospace vehicles. The fuel vapor generated in the fuel tank is mixed with the liquid fuel from the tank. The mix is compressed and supplied to the engine system as usable fuel. The compressor used for compressing the combination gas and liquid can be driven from a turbo expansion cycle using aerodynamic heating of the vehicle. Several different embodiments for mixing the fuel vapor with liquid fuel are disclosed.

Abstract: Method for fabricating a laminated coil conductor for a high current coil which includes wrapping a layer of insulation around a rotatable shaped mandrel and then winding a plurality of copper sheets over the insulation as the mandrel is rotated. Solder is interposed between the copper sheets and between coolant tubes positioned on each end of each coil conductor. The assemblage is then removed from the mandrel and raised to a temperature to bond the copper sheets and coolant tubes together. The assemblage is then placed in a structural box and a plastic is injected into the box to fill any voids between the coil conductor and the box.An assembly of a plurality of coil conductors arranged in a high current coil according to the method is illustrated.

Abstract: An improved wind tunnel six component balance that is capable of accurately measuring low loads and high loads. The variable range balance has low load axial elements that will measure low loads precisely. When the load is increased over the low range capability of the measuring elements, in either the positive or negative load direction, pressure is applied to either the forward or aft bellows that are mounted in the inner tubular rod of the balance. This pressure applies a counter balance in force that reacts against the load applied. The results of this force is that the low loads links will always stay on range.

Abstract: A method of making a composite structure, such as an aircraft wing, which has a foam core and at least one outer layer of fiber reinforced resin material. A shaped foam core is prepared by compressing a rigid, closed-cell foam to the desired shape in a closed mold under heat and pressure. A sheet of flexible open-cell foam is impregnated with a thermosetting resin. A sheet of dry fiber reinforcement material is placed on one or both sides of the impregnated foam sheet. The resulting sandwich is wrapped around the foam core and the assembly is placed in a corresponding tool cavity. The tool is heated to the curing temperature of the impregnating resin. As the temperature rises, the foam core expands, exerting pressure on the impregnated foam sheet, forcing resin into the fiber reinforcement, wetting all the fibers and forcing air out of the material. As the resin cures, void-free, strong skins are formed integral with the core foam.

Abstract: In one embodiment a bundle of optic fibers of different lengths are inserted through the case wall of a solid fuel or a hybrid rocket motor and extends through the wall of the fuel grain to the edge of the bore in center thereof. As the grain burns in a normal manner, from the center toward the outer periphery of the case, the bright flame of ignition is seen at the end of the fiber optic fiber adjacent to the flame. The length of each fiber in the bundle is used to determine the burn rate and amount of grain left to ignite. In another embodiment different length fibers of a bundle are looped into the grain and back to the exterior of the case and light emitting diodes are positioned at one end of each fiber with a light-detecting means at the other end. The light through the diodes is monitored to detect a no-light condition which exists when a fiber is destroyed by the burn. In yet another embodiment a single optic fiber is used with a light source and a light reception means at one end.

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: An adaptive gain and phase controller for an autopilot for a flight vehicle, such as a hypersonic glide vehicle, that includes applying a reference excitation signal to the control system of a flight vehicle, measuring the response of the vehicle to that excitation signal, namely the gain and phase losses through airframe, and making adjustments to the gain and phase inputs to the autopilot based on those measurements. A high gain narrow bandpass filter is incorporated so that the test signal can be extracted from the airframe of the flight vehicle.