Abstract: The present invention provides a simulant material comprising a primary explosive and a carrier.

Abstract: A shaped, flexible fuel and energetic system is presented. The shaped, flexible fuel comprises at least one polymeric binding material and porous silicon particles dispersed throughout the polymeric binding material. The porous silicon particles are prepared from a metallurgical grade silicon powder. The shaped, flexible fuel preferably includes shapes such as: an article, a film, a wire and a tape. The energetic system comprises the shaped, flexible fuel portion used alone or in combination with at least one oxidizer.

Abstract: The present invention provides pyrotechnic grains of composition comprising at least one oxidizing charge and at least one reducing charge and no binder. In characteristic manner, said grains are in the form of substantially cylindrical blocks: with a thickness of more than 5 mm; with an equivalent diameter of 10 mm or more; and with porosity in the range 1% to 8%, limits included. Said grains, advantageously based on guanidine nitrate and basic copper nitrate, are suitable for the slow, low-pressure generation of gas over an extended period.

Abstract: Perchlorate-free green flare compositions are disclosed which, when burned, produce green smoke and flames. Methods of producing the compositions are also disclosed.

Abstract: A shaped, flexible fuel and energetic system is presented. The shaped, flexible fuel comprises at least one polymeric binding material and porous silicon particles dispersed throughout the polymeric binding material. The porous silicon particles are prepared from a metallurgical grade silicon powder. The shaped, flexible fuel preferably includes shapes such as: an article, a film, a wire and a tape. The energetic system comprises the shaped, flexible fuel portion used alone or in combination with at least one oxidizer.

Abstract: Lithium fuel pellets are coated with a fluorinated oil, rather than a fluorinated polymer or telomer. The lithium pellets are coated by placing the pellets inside the lithium reaction vessel and then pouring a fluorinated oil into the reaction vessel. The reaction vessel is rotated in order to evenly coat the lithium pellets. The oil adheres to the lithium pellets and does not settle to the low point of the boiler cavity.

Abstract: Gas generating compositions having a fuel preferably comprising a mixture of 5-aminotetrazole (5-AT), azodicarbonamide (ADCA), an oxidizer, and a superfine metal powder burn rate enhancer such as nano-aluminum, for use in automotive seatbelt pretensioners and other suitable applications requiring high impetus, high rate of gas generation. Also, methods of making these compositions, and devices incorporating them such as seatbelt pretensioners.

Abstract: This invention relates to energetic compositions, which offer increased performance in conjunction with a total absence of hydrogen chloride in the combustion products. The formulation avoids the use of halogen based oxidizers to prevent the formation of halogen based byproducts. The formulations disclosed herein use ammonium dinitramide as a primary oxidizer, which is a more energetic molecule than ammonium perchlorate. The solid propellant formulations disclosed herein comprise about 5 to about 10 weight % of at least one energetic binder, about 20 to about 35 weight % of an energetic plasticizer; about 25 to about 45 weight % of ammonium dinitramide as a primary oxidizer; about 0 to about 20 weight % of particulate aluminum having a particle size of about 1 &mgr;m to about 60 &mgr;m; and about 0 to about 20 weight % of ultrafine aluminum having a particle size of less than 1 &mgr;m.

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: A fire suppressant composition is provided which exhibits a low pressure and low flame temperature. The composition comprises ammonium nitrate and a guanidine salt or derivative which produces greater than 3 moles of inert gas per 100 grams of composition and alkali metal or alkaline earth salts for flame suppression. The composition may also include iron or iron oxide.

Abstract: A coating for a gun propellant powder wherein the graphite commonly used to coat a gun propellant powder is totally or partially replaced with molybdenum disulfide in an amount equal to or less than five tenths percent by weight of the propellant powder.

Abstract: Tungsten is added to fuel gels to increase the density specific impulse. l gels contain monomethylhydrazine or other hypergolic liquids well known in the art. The quantity of tungsten employed can vary from 10%-98% weight percent depending on the specific application. The important parameters to consider during formulation are particle size, concentration, combustion efficiency, physical properties, and plume signature. Tungsten particle sizes ranging from 10 microns to 0.5 micron were compared with carbon of 0.24 when burned in air. It is shown that tungsten burns as well as or better than carbon; however, the increased density specific impulse achieved with tungsten as compared with carbon verifies that tungsten as a high energy additive to hypergolic fuel gels is superior.

Abstract: Energetic compositions and the process for obtaining same for use as the itable composition in infrared-emitting decoy flares, for high-temperature ignition compositions, and the like, are disclosed. These compositions are attained by combining a fluorinated hydrocarbon, either in a liquid state or as a water emulsion, with a powdered metal fuel such as aluminum, magnesium, titanium or zirconium to yield volatile solvent free energetic compositions.

Abstract: Energetic compositions and the process for obtaining same for use as the itable composition in infrared-emitting decoy flares, for high-temperature ignition compositions, and the like, are disclosed. These compositions are attained by combining a fluorinated hydrocarbon, either in a liquid state or as a water emulsion, with a powdered metal fuel such as aluminum, magnesium, titanium or zirconium to yield volatile solvent free energetic compositions.

Abstract: A PBAN-based solid rocket motor propellant which includes more than 85% or more solids is provided. Propellants of this nature are possible using the combination of diepoxide curing agents and PBAN as a binder. The curing agents include diepoxides having 4 to about 10 carbon atoms. It has been observed that when a diepoxide curing agent is substituted for conventional curing agents, viscosities are significantly reduced, thus enabling the addition of higher percentages of solids in the propellant formulation. Total solids loading of over 85% are achievable while maintaining end-of-mix viscosities within acceptable ranges.

Abstract: The present invention relates to the field of gas-generating pyrotechnic compositions intended for motor vehicle safety.The compositions according to the invention include:an oxygen-containing thermoplastic binder and especially a block aliphatic copolymer of formula: ##STR1## in which: PA is a polyamide block,PE is a polyether block,n is a number between 2 and 10,an energetic plasticizer which is a polyglycidyl azide,an oxidizing charge in which at least 85% of its weight consists of ammonium nitrate.The compositions according to the invention burn without solid residues and can be employed in gas generators without a filter chamber.

Abstract: A stable chlorine-free solid rocket propellant composition containing a low energy binder component having an HEX value not exceeding about 0 cal/gm and comprising, in combination, a nitrate salt and/or phase stabilized nitrate salt as oxidizer component, a Mg/Al alloy of limited Mg content as a fuel component, at least one energetic plasticizer component, and a burn rate catalyst.

Abstract: Scavenging and neutralization of HCl from the exhaust plume of a solid grain rocket motor is achieved by including elemental magnesium as the sole metallic component. The magnesium acts both as a propellant fuel and as a scavenger of halogen acids derived form the halogenic oxidizer. Combustion of the high energy propellant produces an exhaust plume from which the halogen acids are scavenged.

Abstract: A solid propellant acts in a chamber to propel a member such as a rocket, the chamber being closed to the atmosphere. The propellant provides high density-impulses and, when combusted, produces end products which do not have any deleterious effects. The propellant includes a binder/reducing agent having hydrocarbyl linkages including --CH.sub.2 -- and a lead compound oxidizer formed from an inorganic lead oxidizer salt. The oxidizer has dense characteristics and stable properties at ambient temperatures and through a range of temperatures above ambient. A second oxidizer made from a metallic salt (not including lead) such as potassium perchlorate may also be included in the propellant. Carbon, preferably in particulate form, may also be included in the mixture as an additional reducing agent. The different materials are included in the propellant in relative amounts by weight to reduce the lead salt in the oxidizer to lead oxide.

Abstract: High performance solid propellant compositions producing halogen-free exhaust products comprised of Ammonium Nitrate and powdered magnesium and optionally containing polyoxypropylene glycol as a binder.

Abstract: Gem-difluoroamino compounds are employed as a partial or complete replacement for TVOPA (trisvinoxypropyl adduct), tris-1,2,3-[bis(1,2-difluoroamino)-ethoxy]propane, in accordance with the nomenclature established by the International Union of Pure and Applied Chemistry. A partial or complete replacement of the vicinal-(1,2-)difluoroamino plasticizer of a difluoroamino-based propellant with its structural isomer or a related structural isomer, namely, a geminal-(1,1-)bis-difluoroamino compound has resulted in two beneficial effects, namely, a marked reduction in pressure exponent and an enhancement of the burning rate of the propellant. Representative of the geminal compounds are the compounds identified as SYEP and SYPO and further identified by the following structural formulas and chemical nomenclatures:SYEPF(NO.sub.2).sub.2 C.CH.sub.2.O.CH.sub.2.C(NF.sub.2).sub.2.CH.sub.2.O.CH.sub.2.C(NO.sub.2).su b.

Abstract: The invention is directed to a primer/detonator acceptable for use in an automobile air bag system.

Abstract: Ultra-ultrahigh burning rate composite modified double-base propellants are btained by use of porous ammonium perchlorate as a replacement for the ultra-ultrafine ammonium perchlorate. The porous ammonium perchlorate is used in combination with aluminum powder fuel and aluminum staples, nitroglycerin as an explosive plasticizer, triacetin as a non-explosive plasticizer, stabilizers selected from resorcinol and 2-nitrodiphenylamine and other selected additives for achieving desired processing, mechanical, ballistic, and other properties of the propellant.

Abstract: Mechanical enhancement of the burning rate of solid propellants is achieved y the incorporation of limited percentages of gas-generated-expandable beads into the solid propellant composition during propellant mixing and which are chemically crosslinked during propellant curing to a solid propellant grain. When the flame front reaches an individual bead during propellant grain burning, the bead which contains a blowing agent selected from 4-toluenesulfonyl hydrazide and 4,4'-oxybis(benzenesulfonyl hydrazide) and coated with a bead forming material consisting of about 95 parts by weight hydroxyl-terminated polybutadiene prepolymer, of about 5 parts by weight of trimethylolpropane, and of about 6 parts by weight of isophorone diisocyanate expands to several times its volume and ruptures. Bead expansion or rupture causes a disruption of the propellant's surface, and the flame can penetrate into the propellant. The penetration results in a major increase in burning rate.

Abstract: A method of making a ferric oxide burning rate catalyst that results in a highly active, finely divided burning rate enhancing catalyst. An iron-containing compound that is capable of vaporization at a temperature below about 500.degree. C. is vaporized. A mixture comprising the vaporized iron-containing compound is combusted with a gas that is capable of supporting combustion in an oxygen environment and does not condense below about 100.degree. C. The ferric oxide burning rate catalyst made by this process is particulary adapted for use in a composite solid rocket propellant. This process provides an ultra pure, highly active, finely divided burning rate catalyst.

Abstract: A highly active, finely divided ferric oxide burning rate catalyst and method for making the same. The catalyst is made by vaporizing an iron-containing compound that is capable of vaporization at a temperature below about 500.degree. C., and is capable of forming ferric oxide when reacted with an oxygen-containing atmosphere at temperatures below about 500.degree. C. The iron-containing compound is then oxidized in an oxygen-containing atmosphere. The ferric oxide burning rate catalyst made by this process is particularly adapted for use in a composite solid rocket propellant. This process provides an ultra pure, highly active, finely divided burning rate catalyst.

Abstract: The mechanical burning rate accelerators, e.g., graphite linters or alumi whiskers, which are employed to enhance the burning rate of solid propellants are modified by depositing specks of metal selected from the group of metals consisting of iron, vanadium, or palladium on the graphite linters or aluminum whiskers. An increase in burning rate of the propellant composition is achieved when the modified mechanical burning rate accelerators in an approximately equal percentage by weight is substituted for the unmodified graphite linters or aluminum whiskers in the propellant composition. During the propellant burning the specks of metal generate localized hot spots of heat which is graphite linters or aluminum whiskers conduct into the propellant and thereby produces the increase in burning rate.

Abstract: Composite solid propellants are provided containing, in an amount effective to reduce the burning rate of the propellant, at least one bitetrazole compound.

Abstract: A heat exchanger 16 for a thermal power source includes a chamber 18 provided with an igniter 28 and a reactant inlet 30. Within the chamber 18 is a mass of lithium pellets 10 and 12, each provided with a coating 14.

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: A melt castable explosive composition not based on TNT is disclosed which consists essentially of about 10 to 20 weight percent of a matrix material having a melting temperature of about 60.degree. to 100.degree. C., up to about 0.5 weight percent of an emulsifying agent and up to about 20 weight percent aluminum powder, balance high explosive. The matrix material is ozokerite wax, ozokerite modified with carnauba wax, or a waxy polyethylene.

Abstract: The binder/charge adhesive of the present invention makes it possible to improve the bonding between the charges and the polyurethane binder of a propellent composition. This agent is an aminoaziridinylphosphine oxide of general formula: ##STR1## in which R.sub.1, R.sub.2, R.sub.3 and R.sub.4 are identical or different and denote a hydrogen atom or a methyl or ethyl radical. The present invention finds application particularly in the field of the manufacture of solid propellent compositions.

Abstract: The glycidyl azide polymer produced by hydrolysis of glycidyl chloride fowed by reaction with sodium azide is employed in a crosslinked composite-modified double-base propellant composition both in the casting powder portion and casting solvent portion as a superior replacement for nitroglycerin in each portion specified. The crosslinked composite-modified double-base propellant composition is characterized by having a greater safety in handling, reduced sensitivity to detonation, higher burning rate, higher specific impulse, and improved mechanical properties as compared with a like composition containing nitroglycerin in the casting powder and the casting solvent portions.

Abstract: A method of making priming devices for a fuel element is disclosed. A high quality priming device is obtained by treating suitable pieces of cellulose with catalyzing agents such as manganates or permanganates and with oxidizing agents such as inorganic oxidizing salts. Such priming devices are very reliable and may be used in portable personnel heaters, e.g. to keep injured people warm after accidents.

Abstract: Improved igniter compositions for rocket motors are provided which, when cured, are non-volatile and are capable of igniting under vacuum conditions and burning steadily at reduced pressures. Said igniter compositions comprise:(a) about 11% to about 13% hydroxyl terminated polybutadiene binder prepolymer;(b) about 0.7% to about 2.0% polyfunctional isocyanate curing agent for said binder prepolymer;(c) about 2.0% to about 20% metallic powder fuel;(d) about 20% to about 40% large particle size ammonium perchlorate;(e) about 30% to about 50% small particle size ammonium perchlorate;(f) about 0.05% to about 5.0% non-volatile burning rate catalyst;(g) about 0.05% to about 0.50% bonding agent capable of wetting the solids in the composition by said binder prepolymer and of chemically coupling with said ammonium perchlorate; and(h) about 0.01% to about 0.20% ammonia scavenger wherein all percentages are by weight based on the total weight of the compositions.

Abstract: Preformed metal/oxidant agglomerates for enhancement of propellant burning ate are prepared from a finely divided metal (aluminum, boron, titanium, etc.), ammonium perchlorate, and a small quantity of the same binder material that goes into the manufacture of the propellant, such as, hydroxyl-terminated polybutadiene crosslinked with a polyisocyanate. Additional ingredients can be incorporated into the agglomerates to bring about further enhancement of burning rate, such as, an ammonium perchlorate decomposition accelerator triphenylbismuthine, a carboranyl burning rate enhancer, iron oxide, etc. Agglomerates are prepared in a fluorinated and/or chlorinated hydrocarbon solvent in which the agglomerate formulation ingredients are insoluble. Any remaining solvent is then evaporated under reduced pressure and the agglomerates are subsequently cured. Optimum mesh size of the agglomerates is 300-500 micrometers.

Abstract: A high energy, high performance, ultrahigh-burning rate composite propell results when 2-azidoethyl acrylate is copolymerized with acrylic acid and is employed as the binder system for the composite propellant. The energetic binder when used in an amount of about 4.25 weight percent of an azido-based propellant composition as compared to a ethyl acrylate binder system results in a specific impulse increase from about 264 (lb-s/lb) to about 275 (lb-s/lb), and a burning rate increase from about 13.7 ips to about 19.8 ips at 1000 psia, and a burning rate increase from about 21.6 ips to about 30.2 ips at 2000 psia. The other propellant ingredients comprise a high solids loading of ammonium perchlorate, aluminum flake and aluminum powder, a burning rate catalyst of carboranylmethyl propionate, graphite linters, the crosslinking and curing agent 4,5-epoxycyclohexylmethyl 4',5'-epoxycyclohexylcarboxylate (ERL-4221), tris-1,2,3[bis(1,2-difluoroamino)ethoxy]propane (TVOPA), and a processing aid of lecithin.

Abstract: This disclosure identifies certain dicarboxylic acids (e.g., maleic and oic) and methods of use to obtain extended pot life in diisocyanate cured polymer systems such as hydroxy terminated polybutadienes, polyesters etc. These compounds also prevent catalysis of the urethane reaction by cure inducing materials such as catocene, iron oxide, ferric floride, etc. without interfering with the function of the cure catalyst triphenylbismuthine.With use of one of these compounds, TPB catalyst can be used even with the more reactive isocyanates. This can be highly desirable since TPB appears to promote the urethane reaction and hence because of this selectivity potentially reduces undesirable side reactions.Typically pot life is changed from 0-2 hours to 12-15 hours.The acids must be preblended with the curing agent 30 minutes to 1 hour for more reactive diisocyanates, and 30 minutes to 3 hours for slow reacting diisocyanates such as IPDI to prevent gassing in the propellant.

Abstract: The invention relates to a cast explosive composition having a relatively high density and energy and a critical diameter no larger than about 150 mm at a temperature of 5.degree. C. The composition comprises inorganic oxidizer salt consisting primarily of ammonium nitrate, a water-immiscible organic liquid fuel, less than about 5% water, a sensitizer and an emulsifier which allows formation of a water-in-oil emulsion at an elevated formulation temperature but which also allows the emulsion to weaken and the inorganic oxidizer salt to crystallize at lower or ambient temperatures to produce a cast composition.

Abstract: The invention relates to a cast explosive composition having a high density, energy and critical diameter and comprising inorganic oxidizer salt consisting primarily of ammonium nitrate, a water-immiscible organic liquid fuel, less than about 5% water, and an emulsifier which allows formation of a water-in-oil emulsion at an elevated formulation temperature but which also allows the emulsion to weaken and the inorganic oxidizer salt to crystallize at lower or ambient temperatures to produce a cast composition.

Abstract: The polyamine compound, TEPAN, a partially cyanoethylated tetraethylene pamine, is reacted with a selected ammonium salt to form an adduct of TEPAN and the selected ammonium salt. The ammonium salt is selected from ammonium perchlorate (AP), ammonium nitrate (AN), ammonium sulfate (AS), and ammonium formate (AF). The process for preparation of the adduct comprises reacting a water solution of the selected ammonium salt with TEPAN while stirring at room temperature. A TEPAN-glycidol derivative product is also reacted with the selected oxidizer salt to form an adduct of the TEPAN-glycidol derivative product.The disclosed adducts (having adduct ratios of 1.0 to 1.8 equivalents of ammonium salt per mole of TEPAN or TEPAN-glycidol derivative product, TEPANOL) improve mechanical properties and processiblity of composite propellant composition containing about 88 weight percent solids (ammonium perchlorate, aluminum, and Fe.sub.2 O.sub.

Abstract: A plasticizer for propellant compositions is 2-hydroxy-3-butoxypropyl oleate. The plasticizer can be incorporated into propellants which conventionally include a binder fuel component, oxidizer component, isocyanate curing agent as well as other conventional components as desired such as bonding agents, curing catalysts and ballistic modifiers. Specifically, a preferred propellant having the internal plasticizer therein includes ammonium perchlorate oxidizer, HTPB binder, aluminum powder fuel, isophorone diisocyanate curing agent, a bonding agent and a delayed quick-cure catalyst. The migration of the plasticizer is substantially reduced so as to extend the shelf-life of rocket motors having the plasticized propellant therein.

Abstract: The subject of the invention is a castable pyrotechnic composition of the type producing smoke with a colored or colorless flame comprising in particular an oxidation-reduction pair and a chlorinated binder. The binder is a high chlorine content resin. It is constituted by the association of a polymerizable chlorinated monomer with a copolymerized or non-copolymerized chlorinated polymer, the resulting mixture being subjected to polymerization at a moderate temperature, said binder then containing 30 to 70% by weight of chlorine.

Abstract: The present invention relates to an improved explosive TNT based composit consisting of TNT, HDX, RDX, aluminum and a small amount of an elastomeric linear polymer having polar groups dissolved or dispersed throughout, said composition having improved properties. Such improved properties include: reduced cracking and exudation, improved friction sensitivity, sympathetic detonation and enhanced cook-off hazard properties.

Abstract: A curable binder for use in forming a castable propellant of the hydroxy-terminated polybutadiene type which uses a combination of two bonding agents, an aziridine polyester and an amine polyester. The amount of aziridine polyester is reduced by a factor of 3 to 4 compared to known systems. Improved propellant properties, including elongation at maximum load and at rupture, while maintaining comparable tensile strength and initial moduli, are obtained. A diisocyanate curing agent, an antioxidant such as di-tert-butylhydroquinone or phenyl-beta-naphthyl amine and combinations of antioxidants, and isodecyl pelargonate as a plasticizer, may be included.

Abstract: A silicon compound as a burning rate catalyst for a solid propellant comption is disclosed along with the solid propellant composition for which the silicon compound is an effective catalyst. The silicon compound is selected from a class of silicon compounds characterized by having one or more silicon bonds selected from silicon to hydrogen bonds, silicon to nitrogen bonds, and silicon to carbon bonds. Representative silicon compounds of the described class of compounds include p-bis(dimethylsilyl) benzene, tris(dimethylsilyl) amine, triethylsilane, hexamethyldisilane, bis(dimethylamino) dimethylsilane, bis(dimethylamino) methylsilane, octylsilane, hexamethylcyclotrisilazane, and dimethyldiicyanatosilane.

Abstract: A solid rocket propellant composition comprising a major amount of ammonium perchlorate, a minor amount of aluminum powder, a minor amount of a binder, and an effective, burn rate modifying amount of Guignet's green pigment or oxidized Guignet's green. Guignet's green pigment increases the burn rate of the propellant without unacceptably increasing the pressure dependence of the burn rate.

Abstract: Plastic bonded self-explosive compositions having improved thermal stability consisting essentially of a self-explosive, e.g., hexanitro-stilbene, which exhibit an exotherm as measured by differential thermal analysis at a temperature no lower than 275.degree. C. and a binder which is a polymer of an alkyl methacrylate wherein the alkyl group has 10 to 20 carbon atoms e.g. lauryl methacrylate.

Abstract: Self-supporting water-bearing explosive products, e.g., for use as primers and in blasting and seismic charges, contain discrete cells of an aqueous solution of an inorganic oxidizing salt and/or of an amine salt encapsulated by a crosslinked (thermoset) resin matrix. The products are sensitized by a dispersed solid high explosive and/or gas bubbles or voids. Preferred primers are sensitized by PETN and are rigid. The products are made by crosslinking a liquid polymer in the continuous phase of an emulsion which contains the aqueous solution as a discontinuous phase.

Abstract: A solid propellant composition employing 2,2-bis(t-butyldicyclopentadienyon)propane (TBD) as the burn rate enhancer in a weight percent from about 2 to about 6 weight percent yields higher threshold values for ignition by impact and improved friction and spark testing values to thereby render the solid propellant composition less hazardous to personnel during handling as compared to similar solid propellant compositions containing Catocene, (2,2-bis(ethyldicylopentadienyliron)propane). The TBD solid propellant composition also comprises from about 9 to about 10 weight percent of hydroxyterminated polybutadiene binder system including an isocyanate curative added in amount of up to 1.0 weight percent and optional modifiers in small amounts with adjustment of the weight percent of other ingredients. Other propellant ingredients comprise a trimodal mix of 200, 1.7, and 0.