Abstract: A material preparation device is provided. The material preparation device includes a bias-ply assembly, a feedstock assembly and an application head. The bias-ply assembly is configured to pass a bias-ply backing material along a first path. The feedstock assembly is configured to pass a feedstock along a second path that crosses the first path at a select angle. The feedstock includes resin pre-impregnated fiber reinforced material (pre-preg) having the fibers at a first orientation relative to an edge of the feedstock. The application head is configured to transfer the pre-preg from the feedstock to the bias-ply backing material at a location where the first path crosses the second path to form a bias-ply with the fibers of the pre-preg having a second different orientation relative to an edge of the formed bias-ply.

Abstract: Disclosed herein are systems and methods for vortex tube desulfurization of jet fuels. Also disclosed are processes for separation of closely boiling species in a mixture of miscible fluids.

Abstract: An injector insert apparatus includes a body that has an inner oil passage that is configured and arranged to allow oil to pass therethrough. The body further has an annular chamber formed around the inner oil passage. The annular chamber has a chamber opening that is configured to be coupled to receive a flow of thermal gas medium. The body also has at least one injector orifice that provides a passage between the annular chamber and the inner oil passage. The at least one injector orifice is configured to inject the thermal gas medium into oil passing through the inner oil passage.

Abstract: A warhead system, method and apparatus. A warhead includes a liner having a longitudinal axis that runs down the center of the liner. The liner includes a liner pattern and a liner shape. The liner shape is selected and a radial distance from the longitudinal axis is selected. The liner pattern is warped as a function of the selected distance and the shape of the liner to reduce the effects of spoking in the post-detonation fragmentation pattern at the selected distance. The liner is then formed as a function of the warped liner pattern.

Abstract: Disclosed herein are supersonic separation systems that can be used for the removal of CO2 from a mixed gas stream. Also disclosed are methods for the separation and subsequent collection of solidified CO2 from a gas stream.

Abstract: A heat transfer system includes an evaporator having a heated wall, a liquid barrier wall containing working fluid, a primary wick positioned between the heated wall and an inner side of the liquid barrier wall, a vapor removal channel located at an interface between the primary wick and the heated wall, and a liquid flow channel located between the liquid barrier wall and the primary wick. Methods of transferring heat include applying heat energy to a vapor barrier wall, flowing liquid through a liquid flow channel, pumping the liquid from the liquid flow channel through a primary wick, and evaporating at least some of the liquid at a vapor removal channel.

Abstract: Apparatus and methods of stretch-forming pre-preg material are provided. In one example embodiment, a variable material stretch-forming apparatus comprises a stretch-forming assembly configured to stretch-form at least one section of a sheet of pre-preg material to a longer length than at least one other section of the sheet of pre-preg material before the sheet of pre-preg material is applied to a tool.

Abstract: Composite material, devices incorporating the composite material and methods of forming the composite material are provided. The composite material includes interstitial material that has at least one of a select relative permittivity property value and a select relative permeability property value. The composite material further includes inclusion material within the interstitial material. The inclusion material has at least one of a select relative permeability property value and a select relative permittivity property value. The select relative permeability and permittivity property values of the interstitial and the inclusion materials are selected so that the effective intrinsic impedance of the interstitial material and the inclusion material match the intrinsic impedance of air. Devices made from the composite include metamaterial and/or metamaterial-inspired (e.g., near-field LC-type parasitic) substrates and/or lenses, front-end protection, stealth absorbers, filters and mixers.

Abstract: A downhole combustor system for a production well is provided. The downhole combustor includes a housing, a combustor and an exhaust port. The housing is configured and arranged to be positioned down a production well. The housing further forms a combustion chamber. The combustor is received within the housing. The combustor is further configured and arranged to combust fuel in the combustion chamber. The exhaust port is positioned to deliver exhaust fumes from the combustion chamber into a flow of oil out of the production well.

Abstract: The present invention provides cyclic nitro compound, pharmaceutical compositions of cyclic nitro compounds and methods of using cyclic nitro compounds and/or pharmaceutical compositions thereof to treat or prevent diseases or disorders characterized by abnormal cell proliferation, such as cancer, inflammation, cardiovascular disease and autoimmune disease.

Abstract: A guard assembly for a tool is provided. The guard assembly has a body with a first open end, a second open end and a mid-portion between the first open end and the second open end. The body forms an inner passage between the first open end and the second open end. The passage is configured to receive a portion of a tool. The body has a plurality of spaced slots. Each slot extends from the first open end a select distance toward the mid-portion of the body. The body has a port and a plurality of openings proximate the second open end to allow air or fluid passage.

Abstract: A solar array including a solar array assembly, hub assembly, and wing assembly.

Abstract: Propellant compositions include an energetic binder, such as nitrocellulose, and a stabilized, encapsulated red phosphorous as a ballistic modifier. The propellant composition may additionally include an energetic plasticizer, such as nitroglycerine. For example, the propellant composition may be formed by mixing a double or multi base propellant that includes nitrocellulose plasticized with nitroglycerine with the stabilized, encapsulated red phosphorus. The propellant compositions may be substantially lead-free and may exhibit improved ballistic properties. Methods of forming such propellant compositions and an ordnance device including such propellant compositions are also disclosed.

Abstract: Gas-generating compositions and methods for their use are provided. Metal complexes are used as gas-generating compositions. These complexes are comprised of a metal cation template, a neutral ligand containing hydrogen and nitrogen, and sufficient oxidizing anion to balance the charge of the complex. The complexes are formulated such that when the complex combusts, nitrogen gas and water vapor is produced. Specific examples of such complexes include metal nitrite amine, metal nitrate amine, and metal perchlorate amine complexes, as well as hydrazine complexes. A binder and co-oxidizer can be combined with the metal complexes to improve crush strength of the gas-generating compositions and to permit efficient combustion of the binder. Such gas-generating compositions are adaptable for use in gas-generating devices, such as automobile air bags.

Abstract: An evaporator may include an outer enclosure and a wick within the outer enclosure. The wick may have an outer lateral side surface positioned adjacent to the outer enclosure and may comprise a plurality of circumferential grooves formed in the outer lateral side surface of the wick and a plurality of channels fluidly connected to the plurality of circumferential grooves. The evaporator may include an outer enclosure and an end cap bonded directly to the outer enclosure, contacting the wick, and having a thermal conductivity that is less than the thermal conductivity of the outer enclosure.

Abstract: Flares with consumable weights connected to a forward end of the grain of the flare are disclosed. Also disclosed are consumable weight components for flares. The consumable weight components include a metal material within a matrix. Also disclosed are methods for fabricating a flare and methods for using a flare. Use of the consumable weights in the flares may reduce the amount of debris falling to ground.

Abstract: Bonding agents for use in formulating solid propellants are described. The bonding agents have a Schiff base, or Schiff base and hydroxyl or amine functionality. These materials are synthesized by reacting a primary amine with an aldehyde to form a Schiff base. By definition, a Schiff base comprises the reaction product of a primary amine and an aldehyde. In one embodiment of the invention, such a product is produced by the reaction of a polyoxyalkyleneamine (JEFFAMINE®) with p-nitrobenzaldehyde and glycidol. The result is a polyether having both hydroxyl and Schiff base functionality. The bonding agents provide superior performance, while avoiding problems, such as ammonia production during processing, encountered when using existing bonding agents. Propellants formulated using these bonding agents have mechanical properties within acceptable ranges.

Abstract: A method of operating a rotorcraft collision avoidance system is provided. The method includes determining a unique characteristic of a detected rotorcraft, determining the actual length of a first rotor based at least in part on the determined unique characteristic of the rotorcraft, locating a major axis of the first rotor of the rotorcraft from a perspective of a home unit, from the perspective of the home unit, determining an angular extent of the major axis of the first rotor, and determining the then current distance from the home unit to the rotorcraft based at least in part on the determined actual length of the first rotor and the corresponding angular extent.

Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.

Abstract: A reactive material for use as a reactive liner in penetrating (shape-charge) warheads and for use in reactive fragments in fragmenting warheads is disclosed. The reactive material comprises an oxidizing agent and a metal filler or metal/metal oxide filler. The oxidizing agent comprises a fluoropolymer having high fluorine content, a low melt temperature, and a high mechanical strength. Preferably, the fluoropolymer is a thermoplastic fluoropolymer, such as a polymer of tetrafluoroethylene, hexafluoropropylene, and vinylidene fluoride. The metal filler comprises a high density, reactive metal. Preferably, the metal filler is hafnium or tantalum. The reactive material is safely processed at temperatures significantly below the thermal autoignition point of the reactive material.