Abstract: Nitramines are one of the more expensive and often the more plentiful ingredients found in energetic materials, such as solid rocket motor propellants, explosives, and pyrotechnics. By treating aluminized energetic material with an aqueous nitric acid solution containing not more than 55% by weight aqueous nitric acid at a weight ratio of aqueous nitric acid to energetic material of about 4:1 to about 6:1, most constituents of conventional aluminized energetic materials are digested into solution, with the exception of nitramines, which remain substantially insoluble in the aqueous nitric acid and can be recovered without requiring recrystallization of the nitramines. A mineral acid other than nitric acid, preferably hydrchloric acid, may be added to increase the rate of aluminum digestion. Treatment of the energetic material can be performed without volatile organic solvents, thus obviating ecological, cost, and safety concerns raised by the use of volatile organic solvents.

Abstract: A rocket motor assembly is insulated or thermally protected with a rocket motor ablative material formed from a prepreg. The prepreg contains at least an impregnating resin matrix and, as a precursor prior to carbonization, either carded and yarn-spun solvent-spun staple cellulosic fibers, solvent-spun cellulosic filaments, or a combination thereof. When patterned and carbonized, the rocket motor ablative material can be lined or otherwise placed into a rocket motor assembly, such as between the solid propellant and case, in the bulk area of the exit nozzle liner, or at susceptible portions of a re-entry vehicle, such as the nose cone.

Abstract: An extrudable black body decoy flare composition which, when combusted, provided black body radiation is disclosed. The compositions generally include from about 40% to about 70% metal such as magnesium or aluminum, from about 10% to about 40% polytetrafluoroethylene, and from about 8% to about 30% binder. Important to the operation of the invention is the production of carbon upon combustion of the composition. Accordingly, polyaromatic thermoplastics, such as polystyrene and dimethyl phthalate, serve as the binder.

Abstract: A propellant cutting assembly and method of using the assembly to cut samples of solid propellant in a repeatable and consistent manner is disclosed. The cutting assembly utilizes two parallel extension beams which are shorter than the diameter of a central bore of an annular solid propellant grain and can be loaded into the central bore. The assembly is equipped with retaining heads at its respective ends and an adjustment mechanism to position and wedge the assembly within the central bore. One end of the assembly is equipped with a cutting blade apparatus which can be extended beyond the end of the extension beams to cut into the solid propellant.

Abstract: Nitramines are one of the more expensive and often the more plentiful ingredients found in energetic materials, such as solid rocket motor propellants, explosives, and pyrotechnics. By treating aluminized energetic material with an aqueous nitric acid solution containing not more than 55% by weight aqueous nitric acid at a weight ratio of aqueous nitric acid to energetic material of about 4:1 to about 6:1, most constituents of conventional aluminized energetic materials are digested into solution, with the exception of nitramines, which remain substantially insoluble in the aqueous nitric acid and can be recovered without requiring recrystallization of the nitramines. A mineral acid other than nitric acid, preferably hydrchloric acid, is added to increase the rate of aluminum digestion. Treatment of the energetic material can be performed without volatile organic solvents, thus obviating ecological, cost, and safety concerns raised by the use of volatile organic solvents.

Abstract: A gas generating eject motor includes a case containing an ignitable low temperature gas generant material that does not produce toxic gases upon the combustion thereof. The gas generant material is generally contained with a screen enclosure housed within the case. An igniter is disposed within the gas generant material for selectively igniting the gas generant to thereby generate combustion gases. A nozzle is disposed within an open aft end of the case for focusing and directing the combustion gases generated by the ignited gas generant material. The case is constructed and arranged to be separably attached to the aft end of a rocket to be launched from a launch platform, so that, upon ignition of the gas generant, the combustion gases focused by the nozzle will apply a thrust to the rocket and thereby propel, or eject, the rocket from the launch platform, at which time the combustible propellant of the rocket motor will ignite and the eject motor will be separated from the rocket.

Abstract: Ceramic liners for use with closed bomb devices are disclosed. The closed bomb devices measure performance properties of energetic materials, such as solid propellant, explosive, and pyrotechnic formulations. The closed bomb devices include a body and a ceramic liner. Alumina silicate and boron nitride are two currently preferred ceramic liner materials which have low compressibility, low thermal conductivity, and excellent durability.

Abstract: A composite tubular article such as a nozzle or a polar boss for a rocket motor wherein straight matrix impregnated yarn portions extend from one end portion to the other in a non-cylindrical ply to achieve increased strength while affording lighter weight. The matrix material may be at least partially curable by actinic radiation to anchor the yarn portions in position as they are applied on a mandrel so that radial rods or the like for anchoring the yarn may be eliminated. For high performance rocket motor nozzle components and the like, the yarn portions may be straight or non-straight and applied by braiding or the like, and the matrix material may be decomposed to a char adequate to anchor the yarn portions and subjected to one or more densification cycles whereby the matrix material may be carbonized.

Abstract: This substantially water-free method for preparing high density igniter granules involves uniformly coating fuel and oxidizer particulates dispersed in a non-solvent with a thermoplastic elastomer solution to produce coated igniter granules exhibiting substantially uniform size and shape distributions. The coated igniter granules are especially useful for waterless extrusion into igniters for automobile gas generating inflation devices, solid propellant rocket motors, and thrust decoys.

Abstract: Thrusting apparatus for guiding missiles or other projectiles. A plurality of side-by-side solid propellant gas generators are provided to discharge axially into a plate which has a rim and a plurality of nozzles which extend radially in the plate and discharge radially from the rim so as to produce thrust normal to the projectile axis on a single plane. The nozzle structure is of laminant construction whereby the materials may be varied from materials which are resistant to high temperature gas flow and erosion in the area of the nozzles and gas flow passageways to medium temperature resistance materials which require good structural properties at other locations for high quality at minimum cost. The configuration also allows minimum volume and length.

Abstract: Apparatus for machining workpiece made of an explosive material, the apparatus including: a drive system and a cutting tool assembly for cutting a workpiece made of an explosive material; an elongate member carried by, and projecting along an axis from, the drive system for holding the workpiece at a machining location while being rotated about the axis by the drive system; and a first shield element interposed between the machining location and the drive system for protecting the drive system against damage in the event of explosion of the workpiece.

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, sufficient oxidizing anion to balance the charge of the complex, and at least one cool burning organic nitrogen-containing compound. 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 ammine, metal nitrate ammine, and metal perchlorate ammine 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: A rocket motor assembly is insulated or thermally protected with a rocket motor ablative material formed from a prepreg. The prepreg contains at least an impregnating resin matrix and, as a precursor prior to carbonization, carded and spun staple cellulosic fibers. When patterned and carbonized, the rocket motor ablative material can be lined or otherwise placed into a rocket motor assembly, such as between the solid propellant and case, in the bulk area of the exit nozzle liner, or at susceptible portions of a re-entry vehicle, such as the nose cone.

Abstract: This rocket motor propellant grain is designed to reduce recession of at least the converging portion of a converging/diverging rocket motor nozzle. The propellant grain has an oxidizer-deficient grain portion constructed and arranged in relation to the nozzle to create, upon ignition of the propellant, a boundary layer of oxygen-deficient combustion products that flows through the nozzle throat passage and over an internal surface region of the nozzle. The boundary layer functions to at least substantially isolate the internal surface region of the nozzle from oxidizers contained in the combustion products generated from portions of the propellant grain having higher concentrations of oxygen than the oxidizer-deficient grain portion. As a result, the oxygen-rich portions of the propellant are unable to react with and thereby cause recession of the nozzle internal surface.

Abstract: The present invention relates to an igniter composition which is capable of being extruded to yield a robust igniter extrudate. The composition is particularly useful in the form of an igniter stick or other selected geometry for use in supplemental safety restraint systems designed for use such as in vehicles, ground or airborne, having such systems.

Abstract: A joint is disclosed for connecting extruded segments to form a container, such as a pressure vessel for storing liquid propane. In cross section, joint includes a pair of symmetrical tabs, each tab configured at the end of adjacent arcuate outer wall segments. Tabs are configured for contiguous engagement to form a boss having a proximate neck portion and a distal body portion. Joint also includes a retaining member configured at the end of an internal web segment. Retaining member is configured to capture boss. A sealing weld is utilized to seal the adjacent tabs at exposed seam.

Abstract: An energetic solid rocket motor propellant having one or more plateau regions of low operating pressure exponent is disclosed. The propellant is formulated from ingredients including an energetic polyoxetane, an effective amount of a plasticizer, an inorganic oxidizer in at least two discrete particle size ranges, and a refractory oxide burn rate modifier.

Abstract: A water slurry method of making high performance explosive compositions and ordnances using the explosive compositions as an explosive ingredient for high performance, low sensitivity explosive applications is disclosed. The method involves combining an aqueous dispersion including CL-20 with a lacquer including at least one non-energetic binder and at least one plasticizer, then agitating the slurry to form CL-20 granules. The CL-20 may be present in the explosive formulation in a concentration of from about 85 wt % to about 96 wt %. The formulation is preferably sufficiently pressable and/or extrudable to permit it to be formed into grains suitable for ordnance and similar applications, including use as grenades, land mines, missile warheads, and demolition explosives.

Abstract: High performance explosive compositions and ordnances using the explosive compositions as an explosive ingredient for high performance, low sensitivity explosive applications are disclosed. The explosive formulation includes CL-20 as an explosive ingredient, and a binder system including cellulose acetate butyrate as a non-energetic binder and bis-dinitropropyl acetal and bis-dinitropropyl formal as an energetic plasticizer. The CL-20 may be present in the explosive formulation in a concentration of from about 85 wt % to about 96 wt %. The formulation is preferably sufficiently pressable and/or extrudable to permit it to be formed into grains suitable for ordnance and similar applications, including use as grenades, land mines, missile warheads, and demolition explosives.

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.