Abstract: Method of directly precipitating substantially pure beta HMX from a substantially anhydrous nitric acid solution without forming and recrystallizing polymorphic HMX. HMX dissolved in a solvent consisting essentially of anhydrous nitric acid is added to water which is seeded with crystals of beta HMX to substantially completely precipitate all the HMX from solution as beta HMX without forming crystals of the other polymorphic forms of HMX. A preferred reaction and apparatus for preparing HMX in anhydrous nitric acid is also disclosed.

Abstract: An electrostatic powder spray coating method and apparatus for producing evenly coated continuous films of thermoplastic and thermosetting powders on substrates or parts having electrically conductive geometric complex surfaces enables the use, without the occurrence of "cobwebbing," of significantly higher charging voltages for the spray gun in the spray coating of preheated substrates and parts, thus allowing faster coating lines. The invention features the use of a grounded electrically conductive ring for grounding the ionized field in the powder discharge region of the spray gun.

Abstract: Metal amine complexes are formed from amines adhering to the general formulas ##STR1## by reaction with various metal salts. Prior to reaction with various metal salts, the above amines may first be reacted with a formaldehyde source or with a formaldehyde source followed by an epoxide or with an epoxide or with an epoxide followed by a formaldehyde source. The resultant metal amine complexes are then employed in asphalt compositions in order to increase the overall strength of such compositions.

Abstract: Poly(caprolactone) polymers are provided having molecular weights of 4000 or higher, are used to form propellant binders. When the high molecular weight poly(caprolactone) polymers are used in propellant formulations and cured with isocyanates of adequate functionality, propellants are produced having improved stress and strain characteristics relative to presently formulated propellants having binders of cured, lower molecular weight poly(caprolactone) polymers.

Abstract: An electrostatic powder spray coating method and apparatus for producing evenly coated continuous films of thermoplastic and thermosetting powders on substrates or parts having electrically conductive geometric complex surfaces and enables the use, without the occurrence of "cobwebbing," of significantly higher charging voltages for the spray gun in the spray coating of preheated substrates and parts, thus allowing faster coating lines. The invention features the use of a grounded electrically conductive ring for grounding the ionized field in the powder discharge region of the spray gun.

Abstract: A rocket motor extendible nozzle exit cone, in one embodiment, is made by folding a sheet stock (metal, etc.) development of a membrane in the form of a cone or conical frustum (with a straight meridian) in such manner involving the provision of a plurality of crease lines therein that the aft or larger diameter region of the membrane that is constructed by joining the two longitudinal edges may be collapsed for stowage with vastly reduced overall length, maximum diameter, and with substantially increased rigidity in comparison with the fully deployed unit. In other embodiments, the extendible nozzle exit cone is made as an integral, seamless, free-standing member. In the stowed condition of each of the embodiments, the material comprising the aft portion of the membrane is situated in multiple layers within the forward portion so that deployment is induced by forward-to-aft gas flow of the rocket motor within the cone.

Abstract: An elongated flexible bag is fitted inside templates that have aligned openings therein corresponding in shape to that desired for a solid rocket motor propellant bore. With the bottom sealed, the bag is filled with a multiplicity of solid pieces each having a cross section substantially less than that of the bag. When filled, suction is applied to the bag by a vacuum needle to exhaust air therefrom until the bag is very tight on the solid pieces contained therein. The vacuum needle is then withdrawn, the hole made thereby is sealed, and the templates are removed from the bag. After use in loading a solid rocket motor with propellant, the bag is cut open, the solid pieces are removed, and the bag is peeled out of the bore in the propellant.

Abstract: A segmented rocket motor case includes wedge members for forcing the case segments into position to remove free play at the joint thereof which may otherwise interfere with or upset the missile's guidance system and throw it off target. A lap joint member for such a joint includes a shoulder having a surface for attachment of a membrane seal assembly for a pulsed rocket motor. A through bulkhead initiator communicates from the forward segment via a fitting which extends through the membrane seal assembly with an igniter for the propellant grain within the aft segment to eliminate the necessity of running explosive transfer lines along the outside of the case from a safe and arm device and other controls at the head end of the rocket motor.

Abstract: A tether line is connected between a rocket launched flare and the canopy of a supporting parachute to cause the parachute to collapse and fall to the earth along with the burned out flare upon release of the single support cable.

Abstract: Thermoplastic elastomer particulates, oxidizer particulates, fuel particulates, plasticizers and other propellant formulation ingredients are mixed to produce a dry blend. The dry blend is tightly packed into a rocket motor casing or mold. The dry blend is then heated in place, beginning at the bottom and continuing upward, to fuse the thermoplastic elastomer. During fusion, vacuum and mechanical compaction pressure are used to eliminate interstices. Upon cooling, a solid propellant grain is produced.

Abstract: A high acceleration high performance solid rocket motor grain such as for a ballistic defense missile or rocket assisted projectile comprises a propellant material which includes a highly plasticized binder so that the grain has a solids ratio equal to at least about 95 percent. In order that the grain with such a solids ratio may have adequate strength and withstand high acceleration forces, a reticulated structure is embedded therein. A method of constructing a rocket motor having such a grain is also disclosed.

Abstract: Tagging compounds (which function as both dyes and markers) having the following structures: ##STR1## wherein x is an integer between 0 and 3 inclusive, y is an integer between 1 and 3 inclusive, z is 0 or 1, and R is a straight or branched chain hydrocarbon having from 1 to 5 carbon atoms are disclosed. These compounds can be dissolved in a diluent at a concentration of from about 10 percent to about 30 percent, forming a concentrate which can be further dispersed in an organic liquid to form a final concentration of from about 1 ppm to about 15 ppm of said tagging compound in said liquid. Methods for detecting the presence of a tagged compound in an organic liquid are also disclosed.

Abstract: Internally plasticized elastomeric binders for projectile propellants are cured polyethers containing THF, CYMMO plus BMEMO, BEEMO and/or OMMO mer units. The polyethers are fluid at room temperature and are miscible with nitrate ester plasticizers. Propellant binders prepared from these polyethers are curable, have low T.sub.g 's, good mechanical properties, and I.sub.sp 's comparable to PEG-based binders.

Abstract: An electroless copper plating bath is improved so as to facilitate its regeneration in an electrodialysis cell. The bath includes elevated amounts of an added salt, preferably as Na salt. The elevated sodium ion level serves as additional counter-cation to hydroxyl ion which is produced at the cathode of the electrodialysis cell. The excess anion from the added salt increases the rate of out-migration of by-products, such as formate ions and sulfate ions, relative to hydroxyl ions through an anion permselective membrane.

Abstract: Thermosetting powder coatings are provided which comprise a high epoxide equivalent weight epoxy resin or mixture of epoxy resins, a cure catalyst for the epoxy resin, an acrylic resin and a polyamide resin. These powder coatings are useful for forming corrosion resistant, essentially crack-free coatings on metal cable, especially cable which is subjected to post-tensioning.

Abstract: An elongated flexible bag is fitted inside templates that have aligned openings therein corresponding in shape to that desired for a solid rocket motor propellant bore. With the bottom sealed, the bag is filled with a multiplicity of solid pieces each having a cross section substantially less than that of the bag. When filled, suction is applied to the bag by a vacuum needle to exhaust air therefrom until the bag is very tight on the solid pieces contained therein. The vacuum needle is then withdrawn, the hole made thereby is sealed, and the templates are removed from the bag. After use in loading a solid rocket motor with propellant, the bag is cut open, the solid pieces are removed, and the bag is peeled out of the bore in the propellant.

Abstract: Solutions of microbiocides in cosolvents having alkanol moieties and concentrate compositions of carriers, microbiocides and cosolvents having alkanol moieties are stabilized against UV-catalyzed oxidation by the addition of phenolic antioxidants. The solutions or concentrate compositions are added to polymeric resins and formed, e.g., by fusion, into polymer compositions exhibiting microbiocidal properties.

Abstract: A ballistic test device for simulating propellant and/or bond and/or strain conditions in a high pressure, high strain rate rocket motor. The device uses internal compliant sleeves which allow radial expansion or growth of propellants, liners and insulation or any combination of all three.

Abstract: Provided are microbiocidal solutions comprising an aryl alkanol solvent and a microbiocidal compound dissolved therein. The solutions may be used to impart microbiocidal properties to polymer compositions.

Abstract: A reinforced split-flap hinge for supporting the unpressurized propellant grain of a rocket motor in a high acceleration environment includes a circular piece of material and an afterwardly spaced first annular piece of material bonded to the convex forward surface of the propellant grain, the material of the circular piece of material and the first annular piece of material being chopped fibers of insulating material in a rubber matrix, with a second annular piece of material bonded to the surface of the circular concave piece of material, the convex forward surface of the propellant grain, and the surface of the first annular piece of material, a third U-shaped annular piece of material having first and second skirts extending aft with a first skirt bonded to the surface of the second annular piece of material, the second and third annular pieces of material being made of fabric reinforced polyisoprene, and a fourth annular piece of insulating material made of powder filled polyisoprene positioned between t