Abstract: The disclosure primarily relates to a method of phlegmatizing crystalline or otherwise particulate explosive substances or compositions in which these are included, by first coating the discrete particles with a thin layer of oxazolin wax in order thereafter to carry out a conventional wet-granulation with a true phlegmatization agent or a binder agent, such as one of the wax types included under different explosive standards or a plastic composition. The invention also concerns products manufactured according to said method.

Abstract: An end-burning grain structural arrangement for a solid rocket propellant is formed by two parallel inhibited grain components formed into an "S" shaped cross section. The components form a fully case bonded system and the two components are separated from each other along the "S" which provides stress relief.

Abstract: A process for continuously producing double base propellant powder of a low density (specific gravity 1.15 to 1.275). This process uses a salt-free liquor.

Abstract: The invention relates to a general method of producing progressively burning deterrent-coated powder, more particularly propellant powder for weapons having barrels. According to the method a film-forming, preferably polymerizable deterrent substance is fed to the powder loosely or dispersed in a liquid phase which is thereafter driven off. The invention also relates to a method of giving a deterrent coating to granular powder or powder cut up in to short pieces (so-called tubular powder) in a fluidized bed. Finally, the invention relates to a special deterrent substance in the form of a water-dispersable polyurethane built up on an aliphatic isocyanate and a caprolacton polyester.

Abstract: The invention relates to a combustion inhibitor composition intended to cover partly the surface of blocks of double-base propellant. The inhibitor composition of the invention includes an aliphatic polyurethane obtained by the reaction of at least one polyisocyanate with a mixture of at least one polyetherpolyol containing at least three hydroxy groups per molecule and at least one polymer containing two hydroxy groups per molecule. This difunctional polymer is chosen from lactone polymers, such as poly-.epsilon.-caprolactone and polytetrahydrofuran. The inhibitor composition may also contain gasifiable fillers and an aliphatic plasticizer. The composition has good discreteness properties, while retaining excellent mechanical properties. The present invention has particular application in the field of solid weapon propulsion.

Abstract: A single- or multiple-base powder charge for propellants is made up of at least one powder grain in the form of a shaped mass of powder having at least one internal cavity. The diameters of the internal cavities within the powder grains making up the charge are different and at least a portion thereof is smaller than the critical diameter that corresponds to the ignition pressure and that governs the penetration of the ignition flame into the internal cavities. With this arrangement at least a portion of the internal cavities is ignited with a retardation only by gas pressures that rise above the ignition pressure.

Abstract: An improvement to the process of applying a rocket motor liner to an inside surface of a rocket motor casing by coating the casing with a rocket motor liner composition and then curing the liner composition. Typical rocket motor liner compositions include the product of a hydroxyl-terminated polybutadiene prepolymer; a diisocyanate curing agent for forming urethane linkages with said prepolymer; a trifunctional aziridine bond promoter; a filler; and a curing catalyst comprising maleic anhydride, magnesium oxide, and triphenyl bismuth. This invention may use an alkaline carbon black filler and/or a curing catalyst which does not include magnesium oxide.

Abstract: The invention relates to a general method of producing progressively burning deterrent-coated powder, more particularly propellant powder for weapons having barrels. According to the method a film-forming, preferably polymerizable deterrent substance is fed to the powder loosely or dispersed in a liquid phase which is thereafter driven off. The invention also relates to a method of giving a deterrent coating to granular powder or powder cut up in to short pieces (so-called tubular powder) in a fluidized bed. Finally, the invention relates to a special deterrent substance in the form of a water-dispersable polyurethane built up on an aliphatic isocyanate and a caprolacton polyester.

Abstract: A thin frangible cork barrier conforming to the contour of the burning surface of individual solid propellant grains in a multiple grain rocket motor prevents premature ignition of the protected grain by the heat of combustion of previously ignited adjacent grains and is expelled through the rocket motor nozzle upon ignition of the protected grain. In a second embodiment, the thermal protection afforded by the frangible cork barrier is augmented by bonding to a thermally-protective elastomer layer which is in turn bonded to the propellant grain burning surface. By virtue of the composition and structure of the embodiments, thermal protection is afforded. Upon ignition of a protected grain the thermal barrier breaks up so as to pass readily through the throat of a small motor nozzle.

Abstract: End burning gas generators for use either as propulsion systems or means for generating large volume of gases for various purposes such as the generation of the fuel for a ducted rocket engine, the rapid inflation of air bags for personal protection or recovery of submersed items or the expulsion of projectiles from subsurface launch tubes are currently widely utilized. End burning gas generator grains are ignited at one end of a generally cylindrical charge mounted within a combustion chamber which is fixed with a suitable exhaust means. For many of the applications described above, it is desirable that the gas generator burn in a uniform manner such that a constant volume of gas is generated per unit of time so that the chamber pressure and the mass flow rate of gas remain constant.

Abstract: A solid rocket motor is provided which comprises a rocket case and a centrally ported propellant grain comprising a main portion and a nozzle portion, wherein the main portion is a shaped and cured first propellant and wherein the nozzle portion comprises a shaped and cured second propellant composition having a lower burn rate than the first composition and having a plurality of aromatic amide fibers dispersed therethrough.

Abstract: A solid fuel rocket engine comprises a casing which defines a combustion chamber with a solid propellant charge in the combustion chamber and an insulating layer of a water containing alkali silicate and fibers disposed between the casing and the charge. The layer is a type which will froth at a predetermined temperature which occurs during burn off of the propellant charge so that it increases in its thickness dimension in the area of the hot gases which develop and provides an adequate insulation. A method of producing the layer comprises heating the alkali silicate layer to a temperature in which it becomes plastic and sheathing the propellant charge with the plastic layer. Thereafter the sheath charge is inserted into the combustion chamber casing leaving an annular gap between this layer and combustion chamber casing. Thereafter heat is applied to the vicinity of the chamber to cause the layer to froth and expand to close the annular gap.

Abstract: A method of determining tensile bond strength and lap shear strength betw a liner/insulation material and a propellant composition which is cured to portions of the liner/insulation material.The liner/insulation material is bonded to a propellant composition in a dogbone configuration by positioning a predetermined size of the liner/insulation material in a groove that is constructed in a mold in a transverse direction for a tensile bond strength specimen whereby the propellant is bonded to each side of the exposed liner/insulation material. The lap shear specimen is formed in a mold wherein a predetermined size of the liner/insulation material is longitudinally positioned in a groove that is constructed in a mold.

Abstract: Non-incendive explosive charge for use in flammable atmospheres includes a layer of damp salt as quenching material surrounding a charge enclosed in an inner housing. An outer housing is strong and pliable, being formed of reinforced rubbery material, to resist rough handling yet to be sufficiently pliable to conform to irregular boulder surfaces. The outer housing is pancake-shaped to provide increased contact area and stability. The relatively flat shape further permits insertion of the charge in crevices between boulders.

Abstract: A combustion inhibitor for a double base propellant is described which comprises a polyurethane elastomer having in chemically combined form a compound which is an aliphatic polyester polyol or an aliphatic polyether polyol, or a mixture thereof, which compound contains 2-6 hydroxyl groups per molecule, and an aliphatic polyisocyanate. The inhibitor also contains 0.1-10 parts by weight of mineral fibers or thermostable organic fibers of length between 0.1 mm and 15 mm per 100 parts inhibitor. The inhibitor may contain an organic gasifiable charge and an aliphatic plasticizer.

Abstract: A curvilinear solid propellant gas generator which includes a housing that as a diameter or width that is larger than the length of the gas generator and with a curvilinear solid propellant grain mounted therein to provide a long burning time propellant with a short length housing.

Abstract: An embedment system with controlled shrinkage for use with a composite-modified double-base propellant composition which is comprised of an embedment granule portion in percent by weight of nitrocellulose of about 23.0, nitroglycerine of about 8.8-13.8, triacetin of about 1.2, bisspiro orthocarbonate from about 2.5-5.0, resorcinol of about 1.5, 2-nitrodiphenylamine of about 1.0, ammonium perchlorate (10 micrometers) of about 48.5 and aluminum powder (20 micrometers) of about 10.0 and an embedment resin portion in percent by weight of bisphenol A-epichlorohydrin of about 50.0, epoxidized dimer acid of about 50.0, and a curative which is comprised of equal parts mixture of methylenedianiline, m-phenylenediamine, and i-propyl-m-phenylenediamine with an added accelerator of 2,4-dinitrophenol. This embedment system employs a specific bisspiro orthocarbonate, 3,9-bis(5'-norbornene-2'-yl)-1,5,7,11-tetraoxaspiro[5.

Abstract: Disclosed is a thixotropic flame inhibitor for a rocket propellant grain luding an organic thixotrope in amounts from about 5 parts to about 30 parts into HTPB liquid polymer in amounts from about 70 parts to about 95 parts by stirring at elevated temperatures. After cooling the mixture to room temperature, appropriate quantities of di- or polyfunctional isocyanates and cure catalysts are added to promote cure at room temperature. Fine particulate matter may also be added to increase viscosity. The resulting formulation is a room-temperature curable, thixotropic mixture which will not flow under its own weight when applied to wettable non-horizontal surfaces in appreciable thicknesses, and which, when cured, is suitable as an inhibitor for composite solid rocket propellants. Thixotropy may be controlled by the level of organic thixotrope in the formulation while viscosity may be adjusted by the level of particulate filler; these parameters determine the allowable thicknesses from one-coat applications.

Abstract: A rocket propellant or rocket motor is provided with an insulating layer ween the fuel proper and the inner wall of the housing forming the combustion chamber. The insulating layer is made of a foamed synthetic material. The foaming insulating material is introduced into the housing under pressure after the solid fuel body has been centered in the housing with a spacing between the inner housing wall and the fuel body the front face of which is covered with a synthetic material film for the subsequent removal of the layer of foamed insulating material from the front face of the fuel body. In an alternative method the inner surface of the combustion chamber wall may be coated with a layer of foamed insulating material prior to the introduction of the fuel into the combustion chamber, said layer of foamed insulating material forming a tubular member.

Abstract: An improved rocket motor has a first layer of silicone rubber and a second ayer of an ablative lining placed between the rocket motor casing and the propellant grain. The ablative lining layer contains chopped novoloid fibers 14 microns in diameter and nominally 1 mm in length interspersed throughout a polymeric composition.

Abstract: An end flap construction for a rocket motor prevents hot vapors from enteg the motor void and causing motor ignition.

Abstract: A firedamp-safe propellant charge comprising a pyrotechnical gas-yielding propellant, said propellant coated with a polymer and/or amides of C.sub.2 -C.sub.4 dicarboxylic acids and/or ammonium oxalate, which composition, upon ignition of the propellant, disintegrates into radicals, said coating being present on said popellant in an amount of 15 to 30 weight percent based upon the weight of said propellant charge.

Abstract: The invention describes a rocket motor having a thermal barrier around a sile casing with gaps along the side to permit initial burning on the outer portion of the grain at rupture of the casing and venting prior to burning over the inner bore to avoid explosion.

Abstract: An improved embedment system is disclosed which is comprised of an embedm granule portion in percent by weight of nitrocellulose of about 23.0, nitroglycerine of about 15.0, resorcinol of about 1.5, 2-nitrodiphenylamine of about 1.0, ammonium perchlorate (10 micrometers) of about 45.5, and aluminum powder (20 micrometers) of about 14.0 and an embedment resin portion in percent by weight of bisphenol A-epichlorohydrin of about 44, epoxidized dimer acid of about 20, and a curative which is the condensation product of 2 moles of 1,2-bis(maleimido)ethane and one mole of triaminotriazine of about 36.0. This embedment system has superior characteristics of a high peel strength and greater resistance to penetration by or absorption of carboranylmethyl propionate or casting solvent absorption.

Abstract: Bonding of hydroxy terminated polybutadiene based propellant grains to rocket motor liners and of the liner to the motor case is greatly improved by incorporating an aziridine in a urethane cured hydroxy terminated polybutadiene based liner.

Abstract: A solid propellant restrictor for preventing erosive burning in solid prolant grain critical areas is described. The restrictor is a mixture of hydroxyl-terminated polybutadiene with 1% by weight of dissolved 2,2'-methylene-bis(4-methyl-6-tert-butyl) phenol, dioctyl adipate, triethanolamine, ferric acetylacetonate, carbon black, aluminum oxide, silicon oxide, and toluene diisocyanate, curing at room temperature and illustrates superior hardening, adhesive, and application properties.

Abstract: The invention relates to the field of combustible objects used in weaponry and in particular to the field of combustible cartridge cases.The combustible objects according to the invention are covered with a thin layer of varnish, based on an organic binder, containing hollow microbeads, the said varnish being based on a binder chosen from the group comprising chlorinated rubbers, polyvinylidene chloride, cellulosic binders, glycero-phthalic binders, polyurethane resins and polyepoxy resins. The varnish contains between 5 and 20% by weight, preferably about 10%, of hollow microspheres, relative to the dissolved polymer, and optionally between 2 and 15% by weight of an energy-producing charge having a self-ignition point above 200.degree. C.The combustible objects according to the invention exhibit delayed self-ignition if they are placed in contact with a hot wall, without their thermodynamic properties being adversely affected.

Abstract: A protective surface coating for ammunition having no cartridge casing and ammunition having a combustible cartridge casing. A body of highly porous nitrocellulose is permeated from the outside with a polymer carried by a solvent to form a binder for the body. A layer of metal platelets containing air-pockets is bound to the body with a binding polymer. The metal platelets are covered with an outer coating of a rapidly curing resin. The protective coating is used to prevent the penetration of moisture into the porous cartridge casing or into the powder mass itself and to provide improved stability to heat and flames.

Abstract: Plasticized cellulose polymers comprise a base polymer having a chain of .beta.-anhydroglucose units joined by ether linkages and having ether substituents, with at least one of the units being additionally substituted, by esterification of at least one hydroxyl group, by at least one ester group, which contains at least two carbon atoms and is chemically unreactive.Preferably the ester group contains four or more, most preferably five, carbon atoms. The carbon chains of the ester groups may be straight or branched.These internally plasticized celluloses may be prepared by, for example, reacting the base polymer with a carboxylic acid in xylene or with an acid chloride or anhydride in pyridine. They are useful in particular as inhibitor coatings for rocket motor propellants and in general wherever cellulose polymers are employed.

Abstract: Progressive burning propellant granules are prepared by a process in which the solvent-wet propellant granules are wetted with a mixture of burning rate deterrent and solvent. The burning rate deterrent penetrates the solvent-wet granules. After deterrent coating, the granules are dried to remove processing solvents initially present in the granules.

Abstract: A highly effective liner-barrier is disclosed for use with carborane-conting ultrahigh burning rate propellants. The liner-barrier includes a resinous matrix selected from an epoxy, polysulfide, and a near neutral phenolic resinous liner-barrier composition, and a leafing aluminum flake incorporated therein. When this liner-barrier is applied to the surface of a rocket motor case, or insulation when used, the leafing aluminum flake floats to a region near the surface of the resin. The liner-barrier is cured to yield a leafing aluminum flake sub-surface layer which markedly reduces the permeability of the liner-barrier by the carboranyl burning rate catalysts which results from the migration or diffusion of the carborane from the propellant. The ultrahigh burning rate propellant is compatible with and forms a secure bond to the liner-barrier. These requirements of compatibility and forming a secure bond are essential for the field of use.