Abstract: Composite rocket propellants, in which the base component is a functionally terminated rubber, and case-bonded rocket motors containing same, are provided, wherein cross-link density at, and adjacent at least a portion of the initial propellant burning surface is lower than that throughout the remainder of the propellant to provide greater strain capability at the initial burning surface together with greater propellant strength for higher mass ratio and improved case bonding than possible utilizing a single "compromise" propellant cross-link density of the prior art.

Abstract: A solid rocket propellant comprising (1) ammonium perchlorate, (2) alumin (3) poly(1,2-butylene) glycol, (4) the reaction product of propylene oxide and either trimethylolpropane, hexanetriol or mixtures thereof, (5) 2,3-dihydroxypropyl bis(2-cyanoethyl) amine, (6) hexamethylene diisocyanate, (7) copper chromite, (8) a carboxylic acid ester of either a diol and a monocarboxylic acid or a dicarboxylic acid and a monofunctional alcohol, and (9) sulfur and optionally containing (10) a metal acetylacetonate, (11) 2,4-pentanedione and (12) liquid silicon oil.

Abstract: A castable solid propellant composition suitable for use as a fuel generator for a ducted rocket motor is provided. The binder for the composition is a crosslinked polysiloxane. The polysiloxane polymer which is crosslinked to form the binder has a viscosity measured at 77.degree. F. of from about 12 poise to about 50 poise. The metal fuel for the composition is a mixture of spherical and flake magnesium. The composition contains from about 16% to about 20% polysiloxane binder and from 55% to 63% magnesium fuel. The oxidizer is principally ammonium perchlorate.

Abstract: This invention relates to a combustible sabot and process for its preparan for a spinning tubular projectile. This combustible sabot is prepared in such a way and of such materials that it combusts spontaneously while exiting the gun barrel. The sabot is fabricated from an anhydride cured epoxy binder, boron, molybdenum trioxide, ammonium perchlorate and a metallic fuel selected from either aluminum or magnesium in the presence of a catalyst.

Abstract: A composite-type propellant is disclosed. The propellant contains metal grains having an average grain size of not more than 0.2.mu. as an exothermic agent.

Abstract: Pour-castable composites are disclosed having mechanical properties such that they are useful either as a high-energy explosives or as propellants. The novel composites include (a) either RDX or HMX as a solid highly-energetic ingredient; (b) a hydroxy-terminated polybutadiene based binder; (c) a diisocyanate curing agent, and (d) a compound of the structural formula ##STR1## wherein R is CH.sub.3, CH.sub.3 (CH.sub.2).sub.x or C.sub.x H.sub.(2x+1), and where x is an integer from 1 to 6, alone or mixed with N,N-di-(2-hydroxyethyl)-4,4-dimethylhydantoin as chemically compatible surfactants.

Abstract: A new class of ballistic modifiers and the synthesis thereof is disclosed rein and are used in propellants either individually or as admixtures in percentages of approximately 0.5 to 6 weight percent to impart mesa or plateau burning rate characteristics over a wide pressure range and reduce the temperature sensitivity of the propellants in relation to burning rates. The modifiers are chelate type compounds comprised of lead and/or copper, and various predetermined molar ratios of compounds such as salicylic acid and beta-resorcylic acid.

Abstract: A crosslinked binder for crosslinked double base propellant is provided. The binder is prepared from nitrocellulose having a nitrogen content of 11 to 13.4% N and an intrinsic viscosity of 0.55 dl./gram to 2.0 dl./gram, a polymeric diol having a hydroxyl functionality of 1.9 to 2.1 and a polyfunctional isocyanate having an NCO functionality of at least three. The propellant prepared from the binder exhibits improved mechanical properties without detriment to ballistic performance.

Abstract: Addition of a small amount, for example 1% by weight, of a liquid silicone oil to a metal containing solid rocket propellant provides a significant reduction in heat transfer to the inert nozzle walls eliminating metal oxide slag collection and blockage of the nozzle and increases burning rate by about 5 to 10% improving ballistic performance.

Abstract: Improved green flare compositions which retain acceptable dominant waveleh and purity and produce efficiencies up to about 11,000 cd-s/g. The flare compositions contain magnesium, barium nitrate, boron and a binder.

Abstract: 1. A solid, pyrotechnic composition for dissemination of 3-quinuclidinyl zylete, said composition consisting essentially of 3-quinuclidinyl benzylete and an oxidizer selected from the group consisting of ammonium and alkali metal chlorates and perchlorates, incorporated in a solid foamed polyurethane binder.

Abstract: A pyrotechnic composition which, when burned, produces yellow smoke and yellow flame. The composition is comprised of between 5 and 30 percent of a fuel which is either magnesium or silicon, between 65 and 85 percent of bismuth subnitrate and between 5 and 13 percent of an epoxy binder.

Abstract: A solid propellant grain is converted from a non-conductive filled elasto into a highly-conductive filled elastomer by introducing an effective amount of an alkali metal tungstate or the analogous ammonium salt which, in addition to imparting electrical conductance characteristics, also functions as an oxidizer in the propellant composition. When sodium tungstates, known as tungsten bronzes, or the analogous ammonium salt, are used to replace from 1 to 3 parts of the ammonium perchlorate oxidizer in the propellant formulation, it changes the grain to a highly-conductive grain, and, thereby, permits measuring the continuity of the propellant grain by means of electrical conductance measurements.

Abstract: 1. A composition capable of being cast and cured into a solid propellant prising:(a) an organic compound having as its sole reacting groups two isocyanate groups, and(b) the hydroxy terminated condensation product of a compound having the structure ##STR1## wherein R is alkyleneR' is selected from the group consisting of hydrogen and alkylR' is alkyland a compound having the structure ##STR2## wherein R'" and R.sup.'v are selected from the group consisting of hydrogen and alkyl.

Abstract: A high performance propellant having greatly reduced hydrogen chloride emission is disclosed comprising a minor amount of hydrocarbon binder (10-15%) and at least 85% solids including ammonium nitrate as the primary oxidizer (about 40% to 70%), a significant amount (5-25%) powdered metal fuel, such as aluminum, a small amount (5-25%) of ammonium perchlorate as a supplementary oxidizer and optionally a small amount (0-20%) of a nitramine such as HMX.

Abstract: A fuel-rich solid propellant gas generator is provided containing about 50 to 70% by weight of a boron fuel and about 30 to 50% by weight of an energetic binder containing a polymer of a dinitrofluoromethyl epoxide of the formula ##STR1## wherein R is alkylene of 1 to 4 carbon atoms.

Abstract: 1. A solid propellant fuel composition for rockets comprising ammonium nitrate and a water-soluble compound of alginic acid selected from the group consisting of sodium alginate, potassium alginate, ammonium alginate, triethanolamine alginate and propylene glycol ester of alginic acid as the principal essential ingredients, the alginic acid component being employed in the ratio of about 2.5 to 5.5 parts per 12 parts of ammonium nitrate.

Abstract: Carboranylmethyl alkyl sulfides are disclosed along with propellant compoions which employ the sulfides as plasticizers. The propellant compositions using the carboranylmethyl alkyl sulfides yield high burning rates and possess good physical properties at high and low temperatures. Processability of the propellants are good and the quality of the propellants are quite attractive. Representative of the carboranylmethyl alkyl sulfides (CB plasticizers) are carboranylmethyl ethyl sulfide (CMES), carboranylmethyl n-propyl sulfide (CMPS), carboranylmethyl n-butyl sulfide (CMBS), carboranylmethyl iso-butyl sulfide (CMIBS), and carboranylmethyl iso-propyl sulfide (CMIPS). Mixture and eutectic mixtures of the carboranylmethyl alkyl sulfides are also employed. Eutectic mixtures of CMPS and CMES (20 to 80%) yield very low-melting-point plasticizers which are very attractive for propellants subjected to low temperature environments.

Abstract: A smoke producing composition comprised of about 50 percent of phosphorus, etween 37 and 44 percent of calcium sulfate, between 3 and 10 percent of boron and about 3 percent of a binder.

Abstract: A solid laser oxidizer source suitable for use in a HF or DF chemical laser.

Abstract: A technique for improving the processibility of composite propellants through reduction of the catalytic effect of iron oxide upon the polymer/curing agent reaction.

Abstract: Thin pieces of high energy propellant are potted in a potting material such s isocyanates cured hydroxy terminated polybutadiene, hydroxy terminated polybutadiene, polyurethane, polyester or polysulfide so that they will primarily end burn. The result is a composite structure that can be used to produce cool gases suitable for use in gas generator applications.

Abstract: A castable binder for plastic bonded explosives is disclosed. The binder is ade up of 42 parts by weight of one unsaturated polyester resin, 30 parts by weight of another unsaturated polyester resin and 28 parts by weight of styrene.

Abstract: 1. A cast, combustible composition comprising: granular ammonium nitrate; catalytic amounts of a powdered combustion catalyst intimately mixed with the ammonium nitrate, said catalyst being selected from the group consisting of zirconium hydride, cobalt, nickel, alloys of cobalt, nickel, and zirconium, and the oxides of cobalt and nickel; and an elastic, combustible, crosslinked, resinous fuel consisting of a copolymer which is preponderantly methyl acrylate in sufficient amount to fill the voids between the granules of ammonium nitrate and catalyst.

Abstract: A small amount of lecithin inhibits the reaction of beryllium hydride with the acid groups in carboxy terminated polybutadiene.

Abstract: A potting compound, comprising a low viscosity and low temperature curing licone resin, potassium perchlorate, magnesium and boron, for encapsulating electronic equipment and assemblies and which can be used for destroying the electronic components in emergency situations.

Abstract: A pyrotechnic cloud seeding composition comprising from about 60 to about 85 weight percent silver iodate, from about 10 to about 40 weight percent of a fuel from the class consisting of aluminium and magnesium, from about 5 to about 15 weight percent binder, and from about 0.1 to about 10 percent halogenated organic compound having a melting point of at least about 50.degree. C. One illustrative compound is hexachlorobenzene.

Abstract: A method of preparing high burning rate solid propellant grains that have od mechanical properties and the high burning rate solid propellant grains prepared from a multimodal blend of at least one ultra-high burning rate propellant that has been cured and ground to a predetermined particle size of from about 100 microns (0.1 millimeter) to about 5 millimeters and at least one uncured propellant composition that has high tensile strength and compatibility with the ultra-high burning rate propellant and that serves as a binder for the solid propellant grain when cured. The solid propellant grain which has good mechanical and physical properties and a high burning rate burns with a flame that moves through the grain as a plane wave. Even though the individual components have different burning rates, it is the rate of the plane wave through the grain that is controlled by the averaging of the rate of burning through each of the particles of the multimodal blend and the binder propellant.

Abstract: Crystals of cyclotetramethylenetetranitramine (HMX) are dissolved in a suitable solvent, as are crystals of ammonium perchlorate. The two solutions are then mixed thoroughly and desiccated. This produces cocrystals of HMX and ammonium perchlorate that may be used as an oxidizer in rocket propellant, pyrotechnic materials, or in gas generators. Stoichiometric proportions are 50 parts of HMX to 30 parts of ammonium perchlorate.

Abstract: A selected polybromocompound, when added in an amount from about 1.0 to at 3.0 weight percent to a controllable solid propellant composition, is effective as a reignition suppressant without having detrimental effects on the ballistic properties of the propellant. The mechanism for accomplishing these desired results consists of sweeping away the combustible exhaust products from the propellant's extinguished surface by the non-combustible decomposition gases of a polybromocompound which is selected from diammonium tetrabromophthalate, tetrabromophthalimide, and N-substituted tetrabromophthalimide.

Abstract: An illuminating pyrotechnic composition comprising a stable inorganic combustion-supporting agent, a nitrated carbohydrate as a high energy binder, at least one non-volatile organic combustible compound whose combustion is exothermic overall and, optionally, a metallic constituent. Such a composition is readily ignitable and combustible and is particularly useful in block form in a signal flare or firework.

Abstract: Solid propellant compositions having graphite fibers dispersed throughout the propellant are provided. The graphite fibers augment the burning rate of the solid propellant.

Abstract: 1. A solid composite propellant consisting of 7% to 15% of a carboxyl-terminated butadiene polymer binder, 66% to 82% of ammonium perchlorate, greater than 0% to 18% of aluminum and greater than 0% to 8% of n-butyl ferrocene as a burning rate catalyst, the ingredient amounts being in weight per cent, and wherein the particle size of the ammonium perchlorate is greater than 0 but less than 3 microns in size.

Abstract: The use of an aluminum silicate molecular sieve as a stabilizer in propelts that give off gas during the aging process. An aluminum silicate molecular sieve is added to propellants that give off gases such as N.sub.2, CO.sub.2, CO, F.sub.2 and NO.sub.x during the aging process. The aluminum silicate molecular sieve is selected to have a pore size of less than about 10 angstroms. This brings about absorption of these undesirable gases during the aging process and thereby prevents degradation of the propellant.

Abstract: Finely divided cupric sulfide increases the burning rate, and reduces the pressure exponent of solid propellant compositions.

Abstract: A readily castable explosive composition comprising (1) an explosive such RDX, HMX or perchlorate salts, (2) a readily curable elastomeric polymer such as a copolymer of 2,2-dinitropropyl acrylate, methyl acrylate and at least one member of the group 2-hydroxypropyl acrylate, 2-hydroxyethyl methacrylate, 2-hydroxypropyl methacrylate and 2-hydroxyethyl acrylate, (3) a diluent or plasticizer such as bis(2,2-dinitropropyl)formal and/or bis(2,2-dinitropropyl)acetal and (4) a cross-linking agent such as 2,4-toluene diisocyanate and polymethylene polyphenylisocyanate and optionally containing one or more of the following: fuels, stabilizers, antioxidants, polymerization catalysts and explosive desensitizers.

Abstract: A dual stabilization system for urethane - crosslinked double base propelt. The stabilization system includes N-Methyl-p-Nitroaniline and Aluminum Silicate molecular sieve. The two stabilizers function in a complementary fashion wherein the N-Methyl-p-Nitroaniline reacts with and makes harmless the nitrogen (III) oxide during the propellant aging process. The Aluminum Silicate molecular sieve is selected to have a pore size of more than about 10 angstroms and reacts with and makes harmless the nitrogen (V) oxides, primarily nitric acid, during the propellant aging process.

Abstract: A temperature stable explosive formulation which is comparatively inexpene, moderately energetic and easy to initiate to detonation, which comprises aluminum, potassium perchlorate, diaminotrinitrobenzene, and vinylidene fluoride - perfluoropropene copolymer.

Abstract: Mechanical properties of composite modified double-base propellant are improved by coating fillers for the propellant with a crosslinked, binder insoluble coating having reactive surface isocyanate groups. The reactive isocyanate groups become chemically bound to the nitrocellulose binder of the propellant during propellant cure. Failure of the propellant at the binder-filler interface under conditions of stress is substantially reduced.

Abstract: A priming explosive is produced by mixing an aqueous solution of a finely divided explosive substance such as in colloidal form with a plastic polymeric carrier and a plasticizer whereby the explosive substance is rendered mechanically workable and has little sensitivity to mechanical shock and electrical impulses. The resulting plastic product is then molded by conventional molding techniques into sheets or films and used as a primer, optionally, by itself without any metal parts. The molded product may be applied to a main explosive mass as a coating or as a strip or it can be formed as a condensor of alternating conductive and insulative layers which is detonated by electrical impulse.

Abstract: 1. A propellant formulation comprising the following ingredients:NitrocellulosePrepolymer of polyglycoladipate and 2,4-tolylene diisocyanateNitroglycerinCyclotetramethylenetetranitramineAluminum2-Nitrodiphenylamine.6. A propellant composition consisting essentially of:The prepolymer of polyglycoladipate and 2,4-tolylene diisocyanate;Nitrocellulose, andNitroglycerin.

Abstract: This invention relates to laser fuels and, more specifically, to solid fuels suitable for use in a chemical laser.

Abstract: 1. Compositions suitable for the manufacture of propellants consisting essentially ofA. 15 to 40 parts of a monomer selected from the group consisting of compounds of the formula ##STR1## in which R is selected from the group consisting of hydrogen, methyl and ethyl, and R.sup.1 is selected from the group consisting of ##STR2## in which n is an integer from 1 to 5, and R.sup.4 is selected from the group consisting of H and CH.sub.3, ##STR3## in which R.sup.2 is selected from the group consisting of hydrogen and lower alkyl containing 1 to 4 carbon atoms, and R.sup.3 is selected from the group consisting of hydrogen and lower alkyl containing 1 to 4 carbon atoms,B. greater than 0 and less than 20 parts of a plasticizer for the polymers prepared by polymerizing the monomers of A), said plasticizers consisting essentially of a major proportion of compounds containing groups selected from the group consisting of NF.sub.2 and ONO.sub.2,C.

Abstract: A solid propellant formulation which utilizes the addition of low levels of transition metal fluorides, such as cupric fluoride and ferric fluoride, as a modifying agent to increase the propellant burning rate while simultaneously decreasing its pressure exponent.

Abstract: Composite explosive slurries of good stability and flow properties are obned by dispersing particulate solid components, e.g. RDX, NH.sub.4 NO.sub.3 and Al, in molten TNT in the presence of a small amount of arabinogalactan or gum arabic to inhibit segregation of the suspended solids.

Abstract: This patent describes a novel solid rocket propellant comprising a polyurethane binder, a solid ammonium perchlorate oxidizing agent, and an effective bond improving amount of a bonding agent having the general formula:X.sub.2 N(CH.sub.2 CH.sub.2 NX).sub.n CH.sub.2 CH.sub.2 NX.sub.2wherein n is an integer and can assume values from 1 to 12, and X is hydrogen, cyanoethyl, hydroxypropyl or mixtures thereof with the proviso that at least one of said X groups is hydrogen.

Abstract: Ballistic modification is accomplished by incorporation oxides of lead and in in nitramine double-base propellants.

Abstract: Increasing the critical pressure of composite propellants by admixing into he propellant composition an additive selected from the group consisting of (1) oxides of Group II metals, titanium, aluminum, boron, zirconium, and lead; (2) nitrides of Group II metals, aluminum, and boron; (3) carboxylates, formates, and sulfates of Group II metals, aluminum, calcium, and magnesium; (4) hydrates of the carboxylates, formates, and sulfates of Group II metals, aluminum, calcium, and magnesium; (5) the following fibrous materials, asbestos, quartz, carbon, and boron; (6) the following metal: Group II metals and boron; and (7) mixtures thereof.

Abstract: Fuel-rich propellant compositions, for use in air-augmented rocket propulsion, containing a high-energy fuel component in the form of finely-divided boron, wherein the boron is present in large excess of the amount oxidizable during combustion of the propellant. A major portion of the boron is ejected, largely as free boron particles, together with the combustion products of the propellant and is burned downstream of the propellant by ram air injected into an afterburner combustion zone. The propellant additionally comprises an organic fuel binder comprising an organic polymer, and an inorganic oxidizer salt, preferably ammonium perchlorate, in an amount at least sufficient to maintain stable combustion of the propellant at desired combustion chamber pressures. The propellant compositions may additionally contain small amounts of Mg, Al, or Zr metal as ballistic or afterburner combustion modifiers.

Abstract: The burning rate of an illuminant composition adapted to be used in an illuminating flare and comprising magnesium granules, an inorganic oxidizer and an organic polymeric binder is increased by incorporating therein 0.1 to 5% by weight of tetranitrocarbazole as a burning rate modifier. The incorporation of the tetranitrocarbazole burning rate modifier permits the attainment of a given light intensity with a lesser proportion of magnesium in the composition.