Abstract: An improvement in an inducer for a pump wherein the inducer includes a hub, a plurality of radially extending substantially helical blades and a wall member extending about and encompassing an outer periphery of the blades. The improvement comprises forming adjacent pairs of blades and the hub to provide a substantially rectangular cross-sectional flow area which cross-sectional flow area decreases from the inlet end of the inducer to a discharge end of the inducer, resulting in increased inducer efficiency improved suction performance, reduced susceptibility to cavitation, reduced susceptibility to hub separation and reduced fabrication costs.

Abstract: The present invention provides a vortex-free shrouded inducer assembly comprising a forwardly extended shroud (24) and surfaces (36,38) defining a recess proximate to the forward lip (42) of the shroud for favorably diffusing and mixing the flow (54) tending to recirculate about the outer periphery (30) of the inducer prior to its being discharged through nozzle (40).

Abstract: A solar collector thermal power system 10 which includes thermal energy storage units (22) containing thermal energy storage canisters (28) with the associated heat enhancers and purifiers. A fluid is directed through the canisters to heat a phase change salt contained therein, which stored heat may later be utilized such as in a space station heat engine.

Abstract: A method of cleaning a fuel assembly contaminated with a radioactive alkali metal in which the fuel assembly is subjected to heating with an inert gas followed by being placed under vacuum and finally cooled with an inert gas; the latter two steps being performed in repetitive cycles.

Abstract: A power system heat source applicable to spacecraft and the like is realized in a combination of an integrated solar absorber-thermal storage assembly 10 and a solar energy focusing unit 50. The focusing unit is capable of selectively functioning inflatable pie-shaped wedges 60 which form a cover for the solar energy focusing unit to control collected radiation effectively and reliably.

Abstract: A method for creating population inversions for use in stimulated emission devices which beam combine, beam clean-up, or frequency up-convert electromagnetic radiation. The invention comprises near resonantly enhanced multiphoton pumping of a multilevel quantum medium with pump beams of appropriate intensities and frequencies detuned from the transition frequencies of the medium. The intensities are orders of magnitude lower than those required for non-resonantly enhanced multiphoton pumping. The detuning is smaller for the maximum multiphoton resonance than for the single photon resonances. Appropriate medium decay constants are required for creating a population inversion between energy levels of the quantum medium. The population inversion exists between energy levels of the medium whose energy difference may exceed the energy of any single pump photon energy.

Abstract: A warm gas accumulator system 10 suitable for use in guidance vane-actuator systems of missiles comprising a tank 12 containing a supply of Tridyne gas, which tank 12 includes an internally mounted catalytic bed 26 and an internally mounted heat exchanger 18. A portion of the flow of Tridyne gas being discharged from the tank is first directed through the catalytic bed 26 and heat exchanger 18 for purposes of generating and transferring heat to the remainder of the contained Tridyne gas. Upon completing its circuit, the diverted portion of the flow is then mixed with the undiverted portion of the flow prior to discharge from the tank for pusposes of improving the volumetric flow rate of warm gas accumulator system 10.

Abstract: An improved hollow electrode 10 and hollow electrode working tip 14 for a gas tunsten arc welding apparatus is disclosed. The hollow electrode face is formed as a lune-shaped radial surface 16 having two tapered intersecting cone-shaped angled surfaces 18. The improved electrode working tip provides a controllable stable arc resulting in an improved weld.

Abstract: An injector assembly 10 for injecting propellants into a fluid fueled rocket engine. Injection assembly 10 comprises a plate member 12 with an opening 16 therethrough. Injector element 14 is sealed within opening 16. Oxidizer flows through central bore 18 and through orifices 26 into combustion chamber 27. Fuel flows from passageway 34 into an annular manifold 38 formed at an interface between flanged portion 32 and plate member 12. Fuel is then injected through orifices 42 into combustion chamber 27 where it impinges with the oxidizer at predetermined points in the combustion chamber 27.

Abstract: An apparatus 10 for pointing an optical concentrator 20 in an extraterrestrial environment. A base 12 rigidly supports focal point equipment 16. At least three support means 18 are utilized for connecting the optical concentrator 20 to the base 12. The support means 18 include actuation means 28 for providing differential motion between the base 12 and the optical concentrator 20 and further include gimballing means 32,36 for accommodating the differential motion and independently gimballing the optical concentrator 20 with respect to the focal point equipment 16.

Abstract: An apparatus 10 and method for producing a high-energy laser beam 14'". A low-power, good quality, input laser beam 14 is produced by master oscillator 12. The low-power beam 14 is focused at an input focal point 20 and reflected from turning flat 22 to a power amplifier 24 where it is amplified to a moderate power level. It is then transmitted through a polarization beam splitter 28 and its optical path length adjusted by adjustment means 30,32,34,36 prior to being directed to a phase conjugator 44. A quarter-wave plate 40 causes the phase conjugated returning beam 14" to be orthogonally polarized thereby reflecting it from polarization beam splitters 38,28. Beam 14" is then passed through the power amplifier 24 and focused at an output focal point 50 in a vacuum. The resultant high-power output beam 14'" is produced without significant degradation in the beam quality.

Abstract: An airfoil-shaped blade assembly having a metallic core, thin coolant liner and ceramic blade jacket includes variable-size cooling passages and a circumferential stagnant air gap to provide a substantially cooler core temperature during high temperature operations.

Abstract: A chemical iodine laser system 10 is provided with a reactive iodine producing container (12) for housing a reactive iodine generating composition. Singlet delta oxygen produced by oxygen generator (30) is mixed with iodine atoms and conveyed to a laser cavity.

Abstract: Disclosed is a chemically pumped laser system including means for generating chemicals that react to produce electronically excited molecules used by the laser system.

Abstract: An injector assembly 10 for injecting fuel and oxidizer in a combustion chamber 38 of a fluid-fueled rocket engine. Injector assembly 10 comprises a stationary housing 12, a plate member 14 attached to the housing 12, at least one injector subassembly 18 and actuation means 16. Each injector subassembly 18 includes a plug 44 attached to the housing 12 and a movable elongated throttle means 64 connected to the actuation means 16. When the throttle is at least partially open, fuel flows through inlet 20, orifice 110, inner passageway 66, orifice 112 and finally to the combustion chamber 38. Oxidizer flows through inlet 22, orifice 114, outer passageway 68, orifice 116 and finally to the combustion chamber 38. Controlling the flow of propellants at upstream orifices 110,114 controls the propellant pressure at the downstream orifices 112,116 during thrust level changes and corresponding combustion chamber pressure changes of the engine, thereby maintaining a constant stream momentum and combustion efficiency.

Abstract: A method and apparatus for testing an optical system 64 having an optical axis and a desired optical wavefront. A hologram is formed containing a recording of the desired optical wavefront. The hologram is located on the optical axis. When the hologram 50 is played back, the desired optical wavefront 62 is produced and directed toward the optical system 64. Wavefront 62 is retroreflected from the optical system 64 containing any of the system's aberrations. The retroreflected wavefront 66 is then passed through the hologram. A reference wavefront 60 is produced which is substantially conjugate to the desired optical wavefront. The reference wavefront 60 interferes with the retroreflected desired optical wavefront 66 thereby producing an interference fringe pattern characterizing the optical system under test.

Abstract: An energetic azide-terminated azido compound and a method for producing same is disclosed.

Abstract: An improved orthotic knee brace system for single and multiple posterior, anterior and lateral knee injuries includes first and second depending frameworks for attaching around a human leg, respectively, above and below the knee joint, the frameworks being hingedly interconnected for relative movement during walking. One of the frameworks bears a cammed surface adjacent the other framework, which other framework has a tibia-stabilizing force transfer mechanism in the form of a lever pivoted thereto. One arm of the lever bears an adjustable contact member adapted to contact the cammed surface, while another arm of the lever is pivotably connected to a tibia-bracing component adapted to wrap around the lower leg portion to prevent tibial displacement during knee movement, as in walking. Preferably, each framework has depending side strips connected to wrap-around leg straps, and the strips of one framework have offset members bearing the cammed surfaces.

Abstract: The present invention provides a regeneratively cooled rocket combustor comprising a combustor wall, a plurality of coolant channels extending through the combustor wall and at least one keel-rib extending into each coolant channel from the channel roof and which is bounded on both of its sides by arcuate flutes for providing smooth and continuous surface transition between the keel-rib and adjoining interior surfaces of the coolant channel.

Abstract: This invention relates to a space vehicle 10 in which solar radiation is utilized to generate thrust by virtue of a solar thermal propulsion unit 12. The propulsion unit comprises basically reaction engines 14 including a DeLaval nozzle 22, heating chamber 26, solar window 28 and inflatable paraboloid solar collector 34.