Abstract: A nozzle assembly including a nozzle structure and liner is disclosed. The nozzle structure is made of at least one carbon-based material and includes a nose tip region, a restricted cross-sectional throat region, and an exit cone region that collectively provide an interior surface configured to define a converging-diverging pathway. The liner includes leg and body portions. The leg portion protrudes over an edge or into a groove of the nozzle structure to engage the liner to the nozzle structure. The body portion of the liner covers at least the throat region of the nozzle structure along the flow path to obstruct high temperature combustion products from causing recession of the nozzle structure. The erosion-resistant liner has at least one irregularity that extends, in a continuous manner, radially at least along the leg portion and, optionally, longitudinally along the body portion.

Abstract: Compositions are provided which, when burned, produce significant levels of infrared radiation, but only limited levels of visible radiation. The basic components of the compositions include a binder, an oxidizer, and a fuel, where the binder also acts the fuel. Preferred oxidizers include those compounds which produce large quantities of infrared radiation when the flare composition is burned. Such oxidizers include potassium nitrate, cesium nitrate, rubidium nitrate, and combinations of these compounds. Selection of the binder is important in order to provide the composition with the desirable characteristics identified above. The binder of the present invention does not produce significant soot. At the same time, the binder serves to form a composition which is processible, avoids chunking, and is compatible with the oxidizers used. It has been found that polymer binders which include relatively short carbon chains (1-6 continuous carbon atoms) are preferred.

Abstract: This pressurized-gas storage assembly includes a pressure vessel having a gas storage chamber and access opening, a polar boss extending through the access opening, a plastic liner lining the gas storage chamber, and a fitting body. The plastic liner includes a nipple portion that extends into the polar boss, terminates at an annular rim, and has a screw-threaded radially inner surface region. The fitting body includes a head portion, an extension longitudinally extending from an end of the head portion and having a screw-threaded radially outer surface region, and an annular shoulder. The annular shoulder has an annular recess formed therein, with a compressible O-ring being accommodated within the annular recess.

Abstract: A process for manufacturing a high performance gun propellant containing an energetic thermoplastic elastomeric binder and a high-energy oxidizer is disclosed. The process includes preparing or obtaining a molding powder of the high-energy oxidizer particles coated with the energetic thermoplastic elastomeric binder and extruding the molding powder into the desired gun propellant configuration. The high-energy oxidizer has a concentration in the range from 70% to 85%, by weight, and the energetic thermoplastic elastomeric binder has a concentration in the range from 15% to 30%, by weight. The molding powder has a particle size in the range from 200&mgr; to 2000&mgr;. Typical thermoplastic elastomeric binders include oxetane, oxirane, and nitramine backbone polymers, copolymers, and mixtures thereof. Typical high-energy oxidizers include nitramine oxidizers.

Abstract: The present invention relates to flares and other solid propellant devices, rockets or the like, equipped with an igniter or igniter system which is based in whole in part on an extruded igniter stick.

Abstract: Hexabenzylhexaazaisowurtzitane is converted to tetracetyl, dibenzyl azaisowurtzitane. The benzyl groups are removed by catalytic transfer hydrogenolysis leaving a pair of available nitrogens. The available nitrogens are acetylated, and the resulting intermediate is converted to CL-20 with a strong nitrating agent.

Abstract: A process is disclosed for producing prills comprised of ammonium dinitramide The prills can include, if desired, one or more thermal stabilizers, and processing aid(s). Solid particulate ADN is introduced into the top of a melting column, allowed to melt to form pre-prills while passing through a hot-zone ("heated zone") in the prilling column. The pre-prills are allowed to spheridize in the presence of an upwardly blown inert medium which is counter current to the path of the ADN in the prilling column. The flow is designed not to blow the ADN out of the prilling column. The rate of spheridization (prill formation) can, if desired, be accelerated by providing additional cooling, such as refrigeration, to the cooling zone in the prilling column. The ADN prills are suitable for use in propellants.

Abstract: Compositions are provided which, when burned, produce significant levels of infrared radiation, but only limited levels of visible radiation. The basic components of the compositions include a binder, an oxidizer, and a fuel, where the binder also acts the fuel. Preferred oxidizers include those compounds which produce large quantities of infrared radiation when the flare composition is burned. Such oxidizers include potassium nitrate, cesium nitrate, rubidium nitrate, and combinations of these compounds. Selection of the binder is important in order to provide the composition with the desirable characteristics identified above. The binder of the present invention does not produce significant soot. At the same time, the binder serves to form a composition which is processible, avoids chunking, and is compatible with the oxidizers used. It has been found that polymer binders which include relatively short carbon chains (1-6 continuous carbon atoms) are preferred.

Abstract: A process for synthesizing 4,10-dinitro-2,6,8,12-tetraoxa-4,10-diazatetracyclo-[5.5.0.0.sup.5,9 0.sup.3,11 ]-dodecane ("TEX") involves combining at least one hexa-substituted piperazine derivative with a medium containing at least one nitronium anion source and at least one acid sufficiently strong to generate nitronium anions from the nitronium anion source. According to this invention, TEX yield is significantly improved by pre-heating the medium to 55.degree. C. to about 70.degree. C. and maintaining the medium from 55.degree. C. to about 70.degree. C. to permit the hexa-substituted piperazine derivative and nitronium anions to react and form the TEX. At least one NO.sub.x scavenger is added to the medium, preferably before the addition of the hexa-substituted piperazine derivative, to increase TEX yield.

Abstract: Energetic polymers and methods for their synthesis are provided. The polymers are preferably produced from cyclic ether monomers having 4 or 5 member rings. The cyclic ether monomers preferably include energetic functional groups such that a polymer formed from the monomer is itself energetic. Polymerization is catalyzed by a combination of alkylating salt and alcohol. The preferred salts are triethoxonium salts with anions such as hexafluorophosphate, hexachloroantimonate, and tetrafluoroborate. It is found that by employing the combination of selected triethoxonium salts and selected alcohols that it is possible to produce an energetic polymer with predetermined functionality and molecular weight. The salt is found to scavenge water in the reaction mixture, thus increasing control over the functionality of the final product. The salt-alcohol combination also rapidly initiates polymerization and allows higher molecular weights to be achieved.

Abstract: One embodiment of this novel rocket system employs at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly at lunch. Another embodiment of this novel rocket involves an insensitive munitions approach that does not require use of such retainers by developing different normal and abnormal burn paths. The rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.

Abstract: An ignition enhanced gas generant grain and method of making an ignition enhanced gas generant involving the application of a dry blend igniter composition to a gas generant particle having a wet adhesive surface.

Abstract: A pressure vessel for holding a pressurized fluid such as compressed natural gas ("CNG") includes two end cells and zero or more interior cells. The cell geometry ensures that the cells meet one another at tangential circular surfaces, thereby reducing the tendency of adjacent cells to peel apart. A web secured about the cells includes two sheets that are tangent to the cells. Unused volumes between the cells and the web contain wedges of foam or rubber. A valve provides fluid communication between the interior of the pressure vessel and a pressurized fluid line. The filled weight of one pressure vessel does not exceed the filled weight of a conventional gasoline tank that occupies substantially the same space as the pressure vessel. The pressure vessel may be configured with exterior recesses for engaging conventional gasoline tank straps.

Abstract: An apparatus for measuring seal defects on a seal surface of a rocket motor case field joint is provided. The apparatus includes a base mountable onto the rocket motor case field joint. The base is sweepable circumferentially along the field joint. An axial sweeping mechanism is disposed on the base and is sweepable axially along the case field joint. A measurement probe for measuring the depth of the seal defect is disposed on the axial sweeping mechanism.

Abstract: Igniter compositions and methods of processing are provided which produce or result in relatively little particulate material, as compared to typical igniter compositions used in association with vehicle occupant restraint airbag cushions.

Abstract: A solid rocket propellant formulation with a burn rate slope of less than about 0.15 ips/psi over a substantial portion of a pressure range of about 1,000 psi to about 7,000 psi and a temperature sensitivity of less than about 0.15%/.degree. F. is provided. A high performance solid propellant rocket motor including the solid rocket propellant formulation is also provided. The rocket motor is encased in a high strength low weight motor casing which is further equipped with a nozzle throat constructed of material that has an erosion rate not more than about 2 to about 3 mils per second during motor operation. The solid rocket propellant formulation can be cast in a grain pattern such that an all-boost thrust profile is achieved.

Abstract: The invention relates to a new class of alkoxy silane compounds of the following general formula: wherein R is aliphatic or aromatic having from 1 to about 15 carbon atoms and R' comprises a hydrolyzable alkoxy functionality. These compounds are particularly useful as adhesion promoters when used with adhesives such as, for example, phenylethynyl terminated polyamide or polysufide adhesives. The invention also relates to a method of synthesizing the alkoxy silane compounds defined above.

Abstract: A mechanism for isolating energetic material feed streams from a material processing apparatus includes a deflector conduit having side panels defining a passageway from an entrance to an exit. Openings are formed in the side panels, and deflector baffles are positioned within the passageway adjacent each of the openings. The deflector baffles are arranged obliquely to the side panels so as to permit material to pass through the passageway toward the exit without falling out of the openings, but to deflect flames, propagating through the passageway toward the entrance, out of the openings to substantially prevent the flames from reaching the entrance. A conveyor may be used in conjunction with the deflector conduit to separate the conduit from a material feed hopper. A combustible conduit may be used to direct material into the deflector conduit from the end of a conveyor or from a feed hopper.

Abstract: The present invention concerns an erosion resistant, low signature liner for solid propellant rocket motors and rocket motors having such a low signature liner. The liner combustion products in the exhaust plume have low visibility in the IR and visible light spectra which is essential for use in low signature solid propellant rocket motors. The liner also forms an in-situ protective layer at elevated temperatures for enhanced erosion resistance. These erosion resistant properties eliminate the need for supplemental case insulation which would contribute additional smoke and combustion products to the exhaust plume as well as add additional costs and inert weight to the motor.

Abstract: A formulation is provided which is capable of performing as a liner layer between a rocket motor casing and the propellant grain disposed within the interior of the rocket motor casing. The composition produces relatively little smoke during the operation of the rocket motor and is capable of securely bonding a wide range of conventional propellants to a wide range of conventional casings. In one preferred formulation, the liner consists of from from about 50% to about 75% oxygen containing polymer; from about 3% to about 15% curing agent; from about 5% to about 50% filler and from about 0.01% to about 0.5% cure catalyst.