Abstract: A composite propellant comprises, by weight:A. from 78 to 92% of an oxidizing agent which is at least one of alkali metal, alkaline earth metal and ammonium chlorates and perchlorates,B. from 7.9 to 17.2% of an organic binder which contains oxygen but not nitrogen, andC. from 0.1 to 0.8% of a carbon-containing combustion regulator.This composite propellant is useful as a gas generator for inflatable cushion protection devices because the gaseous combustion products are substantially free from toxic gases.

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: 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.

Abstract: Composite carboxy terminated polybutadiene (CTPB) rubber base propellants, in which the CTPB inherently contains 2,2'-methylene-bis(4-methyl-6-tert-butyl)phenol (A0-2246) added during CTPB manufacture and antagonistic toward conventional antioxidants added to the CTPB propellant, are provided, which contain a synergistic (see Markush definition) antioxidant mixture highly compatible with the inherently present AO-2246. Invention also provides the antioxidant mixture per se.

Abstract: The invention provides epoxy cured rubber based propellants containing one or more N,N'-dialkyl- and/or diarylphenylenediamines chemically locked in the polymeric network to impart improved resistance to oxidative hardening of the propellant surface and inner structure.

Abstract: High density solid propellants are prepared by a process which comprises mixing the solid propellant components comprising a perfluorinated polymer, such as high molecular weight polytetrafluorethylene, and an inorganic oxidizer salt, such as NF.sub.4 BF.sub.4, with a dispersion containing a dissolved low molecular weight perfluorinated polymer, a suspended low molecular weight pefluorinated polymer and a suitable solvent, removing the solvent from the mixture, and drying the solids.

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

Abstract: Trioctylphosphine oxide and tributylphosphine oxide are representative of e phosphine oxide compounds which are utilized in isocyanate curable composite propellant compositions to extend usable pot life required for mixing and processing of the specified compositions. The compositions are comprised of a binder of hydroxy terminated liquid polymer systems, (e.g. hydroxy terminated polybutadiene and the like) optional selected plasticizers, optional metal fuel, and the inorganic oxidizer, ammonium perchlorate, that is substantially of very fine particle size (less than 20 microns).

Abstract: A means for reducing or eliminating the erosive burning which takes place ring the burning phase of solid propelled rocket motors which have a large length-to-diameter ratio and/or slow-burning propellants is disclosed. The means comprises incorporating into the solid propellant, in limited percentages (0.1-1.0%), a silicate selected from talc, kaolinite, kaolin, muscovite mica, and feldspar. The silicate additive is effective for composite or double-base solid propellant compositions. The solid composite propellant compositions can vary widely in formulation ingredients to include numerous ballistic modifiers; however, the general formulation for a composite propellant contains in addition to the silicate, a high solids loading of an inorganic oxidizer such as ammonium perchlorate, a polybutadiene binder with curatives and crosslinking agents, and optional metal fuel, preferably aluminum. The polybutadiene can have carboxyl- or hydroxyl-terminal groups.

Abstract: This invention concerns high energy propellants containing boron compounds which are suitable for use as propellants.

Abstract: A solid propellant gas generator system employing fluorocarbons as the primary binder and fuel and oxidizing salt wherein the oxidizing power resides in the cation to provide ozidizer-compatible combustion products. The thermal output may be tailored by adding small quantities of boron or carbon fuels and the composition of the combustion products may be tailored by varying the ratio of the fluorocarbon to the oxidizer.

Abstract: Disclosed is a solid propellant composition in the form of a munition which comprises an inorganic acid salt in intimate combination with the reaction product of a carboxyl bearing polymer and a glycidyl thioether. The composition is prepared by mixing the oxidizer, carboxyl containing polymer, and glycidyl thioether and curing the resulting mixture to a coherent grain. Unexpectedly, an excellent cure is achieved in the presence of the oxidizer.

Abstract: A flame-explosion couple is disclosed which upon ignition burns for a period of time in a relatively stable manner and thereafter explodes to produce fragments which continue to burn for a further period of time. The composition may comprise from 40 to 89 percent by weight of a volatile liquid fuel, from 10 to 50 percent by weight of a secondary explosive or strong metal salt oxidizer and from 0.5 to 5 percent by weight of an explosive primer. It is usually desirable to incorporate a gellant in the composition to give it a jellylike consistency of a desired viscosity. The composition may optionally contain combustible metal powders and combustible polymers.

Abstract: Polybutadiene-iron carbonyl complexes are useful as the binder-catalyst for ast-burning rate propellants which are additionally comprised of ammonium perchlorate, aluminum powder, curative-cross-linking agent, and additive (e.g., wetting agents, grinding aids, etc.). The complexes, which are regarded as copolymers of uncomplexed polybutadiene and tricarbonyl(diene)-iron units [C.sub.8 H.sub.12 Fe(CO).sub.3 ].sub.x (where x is one or multiples of one), can be utilized as a high burning rate additive or as a plasticizer for carboxylated polybutadiene binder materials, such as, polybutadiene acrylic acid, polybutadiene acrylic acid-acrylonitrile, carboxyl-terminated polybutadiene, and hydroxy- or epoxy-terminated polybutadiene. The various binder materials, such as those set forth above, can be reacted with the polycarbonyl-iron directly to yield a prepolymer which can be used as the binder-catalyst for propellants containing, an oxidizer, metal fuel, curative-cross-linking agent, and additives.

Abstract: A flare composition is passivated to prevent gas generation during curing at elevated temperatures by incorporating therein as a passivating agent a small amount of a polyalkylene oxide phosphate ester. The additive also serves to increase the pot life of the composition.

Abstract: The use of certain chemical constituents, such as hexanitrostilbene, triaotrinitrobenzene, picric acid and the ammonium salt of picric acid, which can be incorporated into propellant compositions which have high pressure exponents to reduce them to acceptable values. The propellant compositions generally include a binder, a curing agent, oxidizer ingredients, and other additives which depend upon the specific structure of a particular propellant formulation.

Abstract: The compound 2-ferrocenyltetrahydrofuran in solid propellant compositions a ballistic modifier. This ballistic modifier increases the burning rate and improves the performance of the particular solid propellant composition in which it is incorporated. The propellant compositions contain in addition to said ballistic modifier, a binder, an oxidizer and a metal fuel.

Abstract: 1. A composition of matter comprised of an epoxy resin, a copolymer of butadiene and acrylic acid, a curing agent, and between about 2.5 and about 30 percent by weight of an inorganic metal salt selected from the group consisting of metal chromates, metal bichromates, metal phosphates, and mixtures thereof.

Abstract: The incorporation of tris(difluoroamino)-methoxyethyl ammonium perchlorate n small percentages in conventional composite solid propellant compositions to achieve a marked increase in burning rates.

Abstract: High energy, low radar attenuation propellant comprising (1) 25-55 weight rcent of a binder which itself comprises from 2-25 weight percent of a copolymer of acrylic acid and a lower alkyl acrylate and 75-98 weight percent of an energetic difluoroamino group containing plasticizer, (2) 0-15 weight percent aluminum or boron (3) 45-75 weight percent of an oxidizer and (4) 1/2-5 weight percent curing agent.