Abstract: An arrangement for attaching and quickly disconnecting and jettisoning a rocket booster from a core space vehicle. The arrangement includes a housing connected at one end to the booster and a segmented nut carried within the housing that threadedly engages a bolt end of an interface mounting clevis secured to the space vehicle. A retainer both locks the segmented nut on the bolt and is responsive to high pressure fluid to slide out of locking engagement with the nut and to urge a conically shaped wedge into a shaped end of the segmented nut to force the segments outwardly out of threaded engagement with the bolt end to disconnect the booster from the space vehicle. High pressure fluid is also applied to a piston having a plunger in engagement with the bolt end so that the bolt end is swiftly driven out of the housing and the booster is thereby jettisoned form the space vehicle. The high pressure fluid is preferably provided by a pyrotechnic device.

Abstract: A combined application paraboloid spacecraft structure that is adapted to serve as a structural element for space transportation vehicles, and in additional applications, as a separated spacecraft. The primary structure of the combined application paraboloid spacecraft structure is shaped as the shell of a paraboloid of revolution which has focusing properties for use in such functions as a solar power concentrator, a surveillance or an astronomical telescope, or a communications antenna when deployed in space. The primary structure of this combined application paraboloid can nest and can also be used to support other single or multiple host spacecraft during launch and orbit to orbit transportation.

Abstract: A self supporting solar concentrator cell array adapted for use in space applications that includes a plurality of cylindric parabolic reflective mirror surfaces, each of which focus recipient sunlight forwardly onto a focal line which is positioned approximately on the backside of an adjacent mirror surface on which is secured a solar element for converting the focussed sunlight into electricity. A front element extending upwardly from the leading edge of each mirror surface cooperates in providing an aperture through which the focussed sunlight passes and side elements close each cell element. The backside of each mirror is provided with a thermally emissive surface to provide mirror thermal control and allows the mirror to act as a thermal radiator fin for the solar cell elements. The mirror surface is provided with a highly reflective coating such as aluminum or silver to optimize reflectivity.

Abstract: A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body in substantially a nose down attitude. The system includes an inflatable bag which is stowed on a portion of a flat annular rim of the aft skirt of the booster. The bag is hinged at opposing sides and is provided with springs that urge the bag open. The bag is latched in a stowed position during launch and prior to landing for recovery is unlatched to permit the bag to be urged open and into sealing engagement with the rim. A source of pressurized gas further inflates the bag and urges it into sealing engagement with the rim of the skirt where it is locked into position. The gas provides a positive pressure upon the interior of the bag to preclude entry of salt water into the skirt and into contact with the engine. A flotation arrangement may assist in precluding the skirt of the booster from becoming submerged.

Abstract: A backup mandrel apparatus to engage the inner surface of a metal tube being welded to support the weld bead and to keep a molten weld puddle from sagging and falling through the tube wall during welding. The apparatus includes a flexible inflatable bladder surrounded by a split expandable mandrel, an expandable band typically surrounding a central portion of the split expandable mandrel, insulation pads surrounding the mandrel adjacent to the expandable band and insulation material covering the inflatable bladder. The insulation pads preferably have a compressed thickness slightly greater than the band thickness. This assembly is inserted within the tubular workpiece to be welded. In use, the inflatable bladder is inflated with low air or water pressure to expand the mandrel to uniformly expand the expandable band to press the insulation pads against the inner side of the tubing workpiece being welded while leaving either no gap or a narrow gap between the band and the inner tube wall surface.

Abstract: An arrangement for controlling the flight of a launch vehicle and a coupled payload, such a spaceplane, from launch to the separation of the payload from the vehicle. The launch vehicle is provided with controllable gimballed rocket engines and optionally with aerodynamic control surfaces, that are controlled by flight control systems. The payload having controlled flight surfaces has control systems that cooperate with those flight control systems carried by the launch vehicle to jointly control the coupled launch vehicle and coupled payload during coupled flight. The cooperating flight control systems provide open and closed loop control systems that react to winds measured prior to launch and atmospheric disturbances as indicated by on-board sensors during flight. The payload is mounted on the launch vehicle at a cant angle relative to the longitudinal axis of the launch vehicle to optimize its lift to the coupled launch vehicle and payload.

Abstract: A centrifugal propellant depot positioned in outer space for storing and transferring cryogenic liquid propellants to and from transfer space vehicles which are adapted to transport cryogenic liquid propellants to the depot to receive the liquid propellants stored in the depot. The depot includes a plurality of contra-rotatable torus-shaped hollow storage tanks adapted to receive cryogenic liquid oxygen and hydrogen propellants that are carried in gas/liquid phase separation by rotational gravity. Transport rail members transversely bridge the storage tanks. A central docking hub is coupled to the transport rail members and disposed centrally of the rotating storage tanks. The docking hub may receive a transfer space vehicle on either of two opposing sides of the hub for transfer, via a transfer vehicle coupled to the rail members, outwardly to the storage tanks.

Abstract: A thermal cycling apparatus having an upper heat chamber and a lower cold chamber positioned vertically beneath the upper heat chamber and vertically coaxial therewith whereby a material to the thermal cycle tested can be transferred between the upper heat chamber and the lower cold chamber. An externally operated flapper door within the thermal cycling apparatus separates the two chambers. The material to be thermally tested is placed in a basket constructed of suitable material which can be translated between the two chambers from a location externally of the chambers. The temperature in the upper chamber is elevated by gaseous nitrogen to a temperature up to about 1000 degrees F. and the lower cold chamber is cooled by a cryogenic liquid. Cycle testing is preformed by alternately transferring the material, i.e. 40 or more specimens at a time, between the upper and lower chambers the number of times desired.

Abstract: A method for continuous processing/in-situ consolidation and curing of thermoset resin impregnated fiber tow into a composite product having minimal porosity and being relatively void free. The method provides for preconditioning a fiber, impregnating a continuous fiber tow with a low viscosity thermoset resin to complete saturation and then simultaneously outgassing and advancing the resin impregnated tow. The preconditioned tow is then applied to a substrate such as a heated rotating mandrel in a filament winding procedure where heat is applied to the nip of the touch-down of the tow to the mandrel with the simultaneous application of pressure for initial consolidation of the tow upon the substrate. Additional pressure and heat are applied to the tow as the mandrel is rotated to provide for advancing the stage of the resin and further consolidation of the material.

Abstract: Communication and computer interconnecting systems using Universal Direct Spherics (Unidispherics) philosophy makes it possible to transmit and store data in an efficient and rapid manner. The system architecture embodies a plurality of communication sites (nodes) which interact with each other by a symmetrical arrangement of great circles on a sphere or their equivalent. Each intersection of two great circles can be a node for linking processors, bulk memories, and in/out units (IND). In addition to the insertion of two great circles on a sphere, there are five other links, four along each of the great circles connected to the nodes at the adjacent great circle intersections and one cross-link to the node diametrically opposite on the sphere.

Abstract: A superconducting conductor assembly using high temperature materials. A double-walled tubular structure has at least one helical strip of superconductive material on the inner wall of the inside tube. Brittle, non-ductile superconducting materials may be used. A coolant, typically liquid nitrogen, is circulated between the tubes to maintain the superconductor below the critical temperature of the superconductor. A buffer layer is preferably included between tube wall and superconductor. A plurality of alternating layers of buffer and superconductor may be used.

Abstract: A passive load limiting strut particularly useful in limiting loads between a spacecraft and an upper stage during booster first stage operation and thereby permit the launching of heavier spacecraft. The strut operates on the principle of snap through buckling of bar linkages. A tension shaft is telescoped into a compression shaft within a housing. A plurality of bar linkages are connected between each of the shafts and the housing, the bars being oriented at an acute angle in the direction of the tension shaft. In tension, the bar linkages connected to the tension shaft progressively buckle, absorbing tension loads. In compression, the bars connected to the compression shaft progressively buckle, absorbing compression loads. A compression spring intermediate the ends of the shafts further aids in load relief. Collars on the shafts prevent the shafts moving beyond preselected locations.

Abstract: An arrangement for attaching, quickly disconnecting and jettisoning a rocket booster from a core space vehicle. The arrangement includes a housing connected to the booster and having a drive means slidably positioned therewithin and selectively locked to a bearing block connected to the space vehicle core by a lockable collet clutch means. The collet clutch means is unlocked by the drive means in response to a selective pressure to disconnect the booster from the space vehicle core and continued movement of the drive means within the housing forces the drive means into a high force contact with the bearing block, causing a rebound which jettisons the housing and connected booster from the core of the space vehicle.

Abstract: An arrangement for measuring the field angle of a magnetic field as a function of axial position within a magnet bore tube of a magnet such as is used with the Superconducting Super Collider (SSC). The arrangement includes a magnetic field alignment gauge that is carried through the magnet bore tube by a positioning shuttle in predetermined increments. The positioning shuttle includes an extensible body assembly which is actuated by an internal piston arrangement. A pair of spaced inflatable cuffs are carried by the body assembly and are selectively actuated in cooperation with pressurizing of the piston to selectively drive the positioning shuttle in an axial direction. Control of the shuttle is provided by programmed electronic computer means located exteriorly of the bore tube and which controls valves provided pressurized fluid to the inflatable cuss and the piston arrangement.

Abstract: The support structure takes the form of a load isolating payload support strut assembly whose length can be selectively shortened between fully extended and fully compressed to vary the spacing between the payload and the booster rocket during different stages of a flight. The strut assembly would allow independent motion of a separately supported booster rocket and payload during ascent, and subsequently provide a rigid interface during the rocket's flight, which would allow an increase in the capacity of space transferred payloads.

Abstract: An apparatus and method for providing a specified amount of heat on a test specimen, a portion of a specimen, or multiple specimens, under space-like conditions. This system includes a vacuum chamber in which one or more test specimens are placed. This chamber is evacuated to the necessary vacuum. One or more external sources of high intensity light is used for providing the necessary temperature. One or more reflectors are used for concentrating the high intensity light. A fiber optic light guide is used for receiving concentrated light from the reflector. A port in the vacuum chamber wall is used so that the second end of the light guide can extend into the chamber so that light exiting the second end impinges on a selected area of the test specimen. A positioning apparatus is used for locating the second end of the light guide within the housing adjacent to vary the test specimen area subjected to the light.

Abstract: The device employs Hybrid Pulsed Transformer principles employing a projectile with an internal pay load. The projectile carries a light weight shorted secondary coil or coils constructed of aluminum and the projectile acts as a moving secondary through a plurality of aligned spaced apart transformer primary coils. The moving secondary coil includes a plurality of surrounding channels containing a liquid, such as water, for cooling. The cooling ability of certain liquids, as for example water, associated with change of state between liquid and gas is employed to cool the coil or coils.

Abstract: An improved mandrel for use in filament winding. Two embodiments are described for a new filament winding mandrel concept. The first embodiment comprises a plurality of spaced apart slots machined at an angle along the ends of the central mandrel section for use with machines of at least three degrees of motion. A second embodiment comprises a series of two circumferential rows of axial fins protruding along the circumference of the central section of the mandrel for use with machines having only two degrees of motion. A second configuration of the second embodiment is an addition of a strip of slots that are simply placed around and secured to the circumference of the mandrel at locations where fiber turn around is desired. This provides for fiber securing in place with minimal rather than requiring machining the axial fins into the tool.

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.