Abstract: A process of generating a gas includes providing an encapsulation of reactive metal particles, releasing the reactive metal particles from the encapsulation, mixing the reactive metal particles in turbulent water, reacting the reactive metal particles in the turbulent water to generate hydrogen, cooling the turbulent water and the hydrogen with water jets, separating solids and liquids from the hydrogen, and providing the hydrogen to an electrochemical cell.

Abstract: A thermal stand-off includes a rigid thermal stand-off section within a spatial region that extends along a distance between a first location and second, opposed location. The rigid thermal stand-off section includes a tortuous solid-wall thermal conduction path that extends from the first location to the second location. The tortuous solid-wall thermal conduction path is longer than the distance of the spatial region. The tortuous solid-wall thermal conduction path can include a tensile spring constant that is greater than a maximum tensile spring constant of a coil spring that fits in the same spatial region and is formed of the same material composition. The tortuous solid-wall thermal conduction path can include an antegrade section and, relative the antegrade section, a retrograde section.

Abstract: An additive manufacturing process includes pressurizing and heating a slurry, flowing the pressurized heated slurry through a nozzle, and depositing the slurry in a predetermined pattern.

Abstract: A selectable ramjet propulsion system for propelling a rocket or missile includes a gas generator adjacent a booster. A frangible diaphragm is disposed between the gas generator and the booster. The booster and fuel gas generator can be operated in normal sequence, or operated at the same time in order to increase the thrust produced for short-range missions. A logic circuit contained on the rocket or missile determines a time to rupture the frangible diaphragm based on whether or not the distance to the target exceeds a threshold distance.

Abstract: A method for the manufacture of a composite fragmenting material having exothermic properties includes the steps of packing a mold with preformed metal fragments; filling interstitial spaces surrounding the metal fragments with a reactive metal powder to form a mixture; and then sintering the mixture at a temperature effective to both coat the metal fragments with the reactive metal powder and to bond the metal fragments together. In one embodiment the composite fragmenting material is formed into a nosecone for a warhead.

Abstract: A selectively submersible vessel includes a combustor, a Stirling engine thermally coupled with the combustor, an electric generator mechanically coupled with the Stirling engine, a rechargeable battery electrically connected with the electric generator, a compressor electrically coupled with the rechargeable battery, a ballast tank fluidly coupled with the compressor, a snorkel fluidly coupled with the compressor, a controller electrically connected with the rechargeable battery, at least one sensor electrically connected with the controller, a data storage device electrically connected with the controller, and a data communications device electrically connected with the controller.

Abstract: A circuit (400, 700, 800) comprising: a first power source (402) supplying first current to a load (470) during a first Period of Time (“PoT”); a second power source (416) supplying a second current to the load during a second POT; a Unidirectional Current Valve (“UCV”) in series with the first power source; a current detector (420, 702, 802) in series with the UCV (422); and a switch (424) in parallel with a series combination of the current detector and UCV to bypass the UCV during the second PoT. The current detector determines whether the second period of time has commenced and whether the switch has closed.

Abstract: An article includes a vessel, a vent connected to the vessel, and a heat flux-responsive plug disposed in the vent and thermally isolated from the vessel. The heat flux-responsive plug has a material selected based on a phase change characteristic.

Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of the DMRJ functioning as an aerodynamic choke.

Abstract: An end-burning grain of a solid rocket motor or other gas-generating device is supplemented with one or more sticks of high-burn-rate propellant embedded in a matrix of a relatively low-burn-rate propellant. The sticks increase the burning surface area as the grain burns by forming conical indentations in the surface.

Abstract: An inducer includes a hub having an inlet end and an outlet end. At least one full size blade has an inner edge is affixed to the hub and an outer edge. This full size blade extends rearwardly from the inlet end in a helical configuration. A partial shroud encloses a first length of the full size blade outer edge adjacent the inlet end. A second length of the full size blade outer edge that is adjacent to the outlet end is free of the partial shroud. It is within the scope of the disclosure to include short blades symmetrically offset from the two full size blades. These short blades have a short blade inner end affixed to the partial shroud and a short blade outer end extending from the partial shroud towards the hub, but terminating prior to reaching the hub.

Abstract: A rocket engine system with a fuel conversion system in communication with a gas generator.

Abstract: A composition includes an alloy that has, by weight, 25-65% zirconium, 25-65% tungsten, and 6-25% of a combined amount of nickel in at least one of iron and cobalt. The alloy may be formed into a geometric body that has a density of 7.8 grams per cubic centimeter to 11.4 grams per cubic centimeter.

Abstract: An article includes a vessel, a vent connected to the vessel, and a heat flux-responsive plug disposed in the vent and thermally isolated from the vessel. The heat flux-responsive plug has a material selected based on a phase change characteristic.

Abstract: A thermal stand-off includes a rigid thermal stand-off section within a spatial region that extends along a distance between a first location and second, opposed location. The rigid thermal stand-off section includes a tortuous solid-wall thermal conduction path that extends from the first location to the second location. The tortuous solid-wall thermal conduction path is longer than the distance of the spatial region. The tortuous solid-wall thermal conduction path can include a tensile spring constant that is greater than a maximum tensile spring constant of a coil spring that fits in the same spatial region and is formed of the same material composition. The tortuous solid-wall thermal conduction path can include an antegrade section and, relative the antegrade section, a retrograde section.

Abstract: A gasification system includes a scrubber in communication with a particulate removal subsystem and a quench sub-system

Abstract: An end-burning grain of a solid rocket motor or other gas-generating device is supplemented with one or more sticks of high-burn-rate propellant embedded in a matrix of a relatively low-burn-rate propellant. The sticks increase the burning surface area as the grain burns by forming conical indentations in the surface.

Abstract: A method for the manufacture of a composite fragmenting material having exothermic properties includes the steps of packing a mold with preformed metal fragments; filling interstitial spaces surrounding the metal fragments with a reactive metal powder to form a mixture; and then sintering the mixture at a temperature effective to both coat the metal fragments with the reactive metal powder and to bond the metal fragments together. In one embodiment the composite fragmenting material is formed into a nosecone for a warhead.

Abstract: To explore deeper expanses of space, rocket ships need rockets that can last twice as long as conventional rockets. Modern rockets use the electric field to attract and accelerate charged particles out and away from the combustion chamber. Space qualified components to increase the electric field are difficult to obtain. Various embodiments of the present subject matter use multiple phases of an input signal into the power supply to cause the output DC voltage signal to be substantially smooth. These smoother signals reduce the voltage requirements of the output diodes and capacitors thereby making them easier to obtain.