Abstract: The invention relates to a fuel component for an explosive, in which case the fuel component contains a volume-expanded molecularly dispersed hydrocarbon, and a method for its production. Furthermore, the invention relates to an explosive formed of the fuel component and an oxidizer, an explosive body filled with the explosive as well as an explosion method.

Abstract: The present invention is a bi-propellant system comprising a gelled liquid propane (GLP) fuel and a gelled MON-30 (70% N2O4+30% NO) oxidizer. The bi-propellant system is particularly well-suited for outer planet missions greater than 3 AU from the sun and also functions in earth and near earth environments. Additives such as powders of boron, carbon, lithium, and/or aluminum can be added to the fuel component to improve performance or enhance hypergolicity. The gelling agent can be silicon dioxide, clay, carbon, or organic or inorganic polymers. The bi-propellant system may be, but need not be, hypergolic.

Abstract: An explosive device and methods for forming same, the device comprising a portion of nitrous oxide and a portion of fuel. In one example, the explosive device may include a first storage area containing said portion of nitrous oxide, and a second storage area containing said portion of fuel, wherein the first storage area selectively maintains the portion of nitrous oxide separated from the fuel in the second storage area prior to detonation of the explosive device. In another example, in the event the explosive fails to detonate, the explosive device may include a vent valve for discharging the nitrous oxide from the explosive device to reduce or eliminate its explosive characteristics. The explosive device can be used for various applications, including but not limited to military weapons, pyrotechnic devices, or civil blasting explosives, for example.

Abstract: Fatty esters of oligoesters of a dicarboxylic acid and a polyol retaining at least one free hydroxyl group, particularly of the formula (I): R1—[OR2O—C(O)—R3—(O)C—]m—R4 (I), where R1 is H, a monocarboxylic acid group, or R6O—[C(O)—R3—(O)C]—; R2s are residues of polyols having at least one substituent free hydroxyl; R3s are hydrocarbylene; R4 is —OH, —OM where M is a salt forming metal, amine or ammonium, —OR6, or —OR2O—R7; R5 is C7 to C21 hydrocarbyl; R6 is C8 to C22 hydrocarbyl; R7 is H, or —C(O)R5; and m is 1 to 20; provided that at least one of R1 and R4 is or includes a C8 to C22 group, are surfactants. A range of surfactant properties can be obtained by varying the molecules within these ranges. Especially where R2 is derived from a higher polyol e.g. sorbitol, R3 is C2 to C6, and the fatty terminal group is C8 to C14, the products can be highly water soluble and effective oil in water emulsifiers.

Abstract: Disclosed are pressure vessels, especially an aerosol container, which comprise an interior that is subdivided into a storage chamber (3) and a propellant chamber (4) and are operated by means of a two-phase propellant. The gas phase (5) of the propellant encompasses carbon dioxide while the liquid phase (6) encompasses polyethylene glycol and/or a (C1-C4) monoether and/or a (C1-C4) diether of a polyethylene glycol, and carbon dioxide that is dissolved therein.

Abstract: An emulsion explosive including a discontinuous phase dispersed in a liquid fuel continuous phase and is provided. The discontinuous phase contains a liquid oxidizer other than an inorganic oxidizer salt. Also provided are articles of manufacture containing the emulsion explosive.

Abstract: A high-energy material composition comprising solid matrix with encapsulated fluid component embedded in the matrix.

Abstract: Nondetonable, or low detonation sensitivity, substantially nontoxic liquid monopropellants are provided. The liquid propellants are formed from aqueous solutions of solid oxidizers in liquid oxidizers and water soluble liquid fuels and formulated to have a freezing point less than ?10° C. Liquid oxidizers may be inorganic or organic aqueous solutions, with hydrogen peroxide being preferred. Preferred solid oxidizers are water soluble nitrates including ammonium dinitramide, aminoguanidine dinitrate, ammonium nitrate, hydroxylamine nitrate, hydrazine nitrate, guanidine nitrate and aminoguanidine nitrate. Preferred liquid fuels are water soluble alcohols, amines and amine nitrates, hydroxyethyl hydrazine, hydroxyethylhydrazine nitrate, cyanoguanidine, guanidines, aminoguanidines, triaminoguanidines, and their nitrate salts, ethanolamine dinitrate, ethylenediamine dinitrate, polyvinyl nitrate, and aziridine.

Abstract: A novel family of amine azides having a cyclic structure therein is disclosed. These compounds have attractive properties as rocket propellants.

Abstract: Hypergolic fuel propulsion systems contain a fuel composition and an oxidizer composition. The fuel composition contains an azide compound that has at least one tertiary nitrogen and at least one azide functional group, as well as a catalyst that contains at least one transition metal compound. The fuel composition optionally further contains a hydrocarbon fuel. The oxidizer composition contains hydrogen peroxide. The transition metal catalyst is preferably selected from the group consisting of compounds of cobalt and manganese. The invention provides a method for propelling a vehicle by providing a fuel mixture that spontaneously ignites with the oxidizer composition in an engine to provide thrust.

Abstract: Inflation apparatuses and methods are provided wherein a hydrocarbon-containing inflation gas-producing mixture is formed via the fluid extraction of the hydrocarbon from a substrate material.

Abstract: A propellant is described for internal combustion-operated tools, especially for setting equipment for fastening elements, based on combustible gases containing isoparaffin and/or synthetic oil based on esters or poly-&agr;-olefins with a boiling point ranging from 120° to 250° C. as lubricant, which can be burned without leaving a residue. Furthermore, a method is described for producing this propellant as well as for using at least one isoparaffin and/or combustible synthetic or, based on esters or poly-&agr;-olefins with a boiling point ranging from 120° to 250° C. as a lubricant, which burns without leaving a residue, in propellant gases based on combustible gases for internal combustion-operated tools.

Abstract: A propulsion device operated in a bi-propellant mode uses a safe hydrogen peroxide as oxidizer and yet has high specific impulse and high response performance. A preheated net 18 is provided in a combustion chamber 14. Both of an oxidizer supply means 10 and a fuel supply means 12 open toward the net 18. Oxidizer 30 and fuel 32 are atomized on the net 18 to thereby increase the surface area. At the same time, the oxidizer 30 and fuel 32 are heated on the net 18 and their decomposition is accelerated. By quickly effecting collision and mixing of the oxidizer 30 with the fuel 32, an instantaneous ignitability can be obtained.

Abstract: Ammonium dinitramide based liquid monopropellants exhibiting stabilised combustion characteristics and improved storage life, containing ammonia, a base weaker than ammonia, or a base which is sterically hindered, added in an amount of 0.1 to 5% of the total weight of the other components of the propellant.

Abstract: Hypergolic fuel propulsion systems contain a fuel composition and an oxidizer composition. The fuel composition contains an azide compound that has at least one tertiary nitrogen and at least one azide functional group, as well as a catalyst that contains at least one transition metal compound. The fuel composition optionally further contains a hydrocarbon fuel. The oxidizer composition contains hydrogen peroxide. The transition metal catalyst is preferably selected from the group consisting of compounds of cobalt and manganese. The invention provides a method for propelling a vehicle by providing a fuel mixture that spontaneously ignites with the oxidizer composition in an engine to provide thrust.

Abstract: Rocket propulsion or rapid response gas generation systems and methods are disclosed in which a novel one component, single tank storable, low toxicity, low detonation sensitivity liquid monopropellant containing a mixture of aqueous 70% hydrogen peroxide, alcohol, and water is catalytically decomposed with an iridium based catalyst. The resulting rapidly formed gaseous decomposition products consisting substantially of carbon dioxide and water vapor are used for rocket propulsion, satellite propulsion, divert attitude control systems for interceptor missiles, and other power control systems where a re-start capability is desired.

Abstract: The reduced toxicity hypergolic bipropellant fuels of the present invention contain a hypergolic fuel and rocket grade hydrogen peroxide oxidizer, preferably HTP. The hypergolic fuel may be a reactive fuel or a catalytic fuel. The rocket grade hydrogen peroxide oxidizer consists of about 90 weight % to about 99 weight % H2O2, more preferably about 94 weight % to 99 weight % H2O2. However, hypergolic ignition may be attained with a H2O2 content as low as 70 weight % for some reactive fuels. The reactive fuel comprises about 6 weight % to 10 weight % reducing agent in a solvent. The catalytic fuel comprises about 6 weight % to 10 weight % catalytic agent in a solvent. The reactive fuels contain ingredients that are intrinsically reactive with rocket grade hydrogen peroxide. Upon contact with rocket grade hydrogen peroxide oxidizer, reactive fuels react vigorously with the hydrogen peroxide resulting in ignition. The catalytic fuels are produced by dissolving a catalytic agent in a solvent.

Abstract: High temperature incendiary (HTI) devices and methods destroy biological and/or chemical agents. Preferably, such HTI devices include dual modal propellant compositions having low burn rate propellant particles dispersed in a matrix of a high burn rate propellant. Most preferably, the HTI device includes a casing which contains the dual modal propellant and a nozzle through which combustion gases generated by the ignited high burn rate propellant may be discharged thereby entraining ignited particles of the low burn rate propellant. In use, therefore, the high burn rate propellant will be ignited using a conventional igniter thereby generating combustion gases which are expelled through the nozzle of the HTI device. As the ignition face of the propellant composition regresses, the low burn rate particles will similarly become ignited.

Abstract: A stabilized water-in-oil energetic emulsion composition comprising a) an aqueous oxidizer phase comprising at least one oxygen supplying component; b) an organic phase comprising at least one organic fuel; c) an emulsifying amount of at least one emulsifying agent suitable for forming a water-in-oil emulsion; and d) an emulsion stabilizer comprising a hydrocarbon polymer, said hydrocarbon polymer having {overscore (M)}n ranging from about 2,000 to about 6,000, provided that said emulsion composition is essentially free of any polyvalent inorganic agent that is capable of cross-linking with the emulsifying agent or the emulsion stabilizer.

Abstract: A propellant gas is described for tools, operated by combustion power, especially for setting equipment for fastening elements, on the basis of combustible gases containing a mixture of (A) 40% to 70% by weight of dimethyl ether, nitrous oxide and/or nitromethane, (B) 8% to 20% by weight of propylene, methyl acetylene, propane and/or propadiene and (C) 20% to 45% by weight of isobutane and/or n-butane.

Abstract: The inventions describes a method and apparatus for remotely forming a mixture of liquid oxygen (“LOX”) and liquid methane (“LNG”), with the mixture commonly referred to as MOX, such that the LOX and LNG never contact each other until inside the container in which the mixture will be used. The method disallows contact between the LOX and the LNG in order to prevent the premature or inadvertent explosive combustion that can occur in a variety of ways. The method provides a way to deactivate the MOX mixture, even after the MOX mixture has been formed. The invention also contemplates various apparatuses that will allow the method to be practiced.

Abstract: The non toxic bipropellent of the present invention contains a non-toxic hypergolic miscible fuel (hereinafter referred to as “NHMF”) and a rocket grade hydrogen peroxide. This NHMF has rapid ignition capability and minimizes the formation of precipitate, even when exposed to extreme heat or water. The NHMF of this invention contains 5 species. Namely, a polar organic species miscible with hydrogen peroxide; a propagator, which may be substituted or unsubstituted amines, amides or diamines; an inorganic metal salt, which reacts to form a catalyst in solution or as a colloid; acetic acid; and alkali acetate. The inorganic metal salt is miscible with the polar organic species and the propagator in solution.

Abstract: Provided is a method for preparing a flowable solid propellant wherein a) liquid oxidizer is added to a tank, b) pellets of cross-linked hydrogel polymer are added to the liquid oxidizer in the tank so that liquid oxidizer is absorbed into the pellets to form flowable combustible pellets and c) the combustible pellets are then flowed into a combustion chamber of a vehicle to combust and the combustion products flow out the propulsion nozzle of the vehicle. Also provided are the liquid oxidizer absorbed flowable combustible pellets so made.

Abstract: An inflator apparatus for inflating an inflatable device and a method are provided wherein a combination of a dissociative gas source material and at least one unreactive dissociation reaction modifier is stored at least partially in liquefied form with the reaction modifier effective to moderate at least one of the temperature and concentration of the at least one gas source material upon the dissociation of at least a portion of the at least one gas source material.

Abstract: A gas generator for air bags having a container holding a combustible gas mixture and fitted with a closure which opens into a combustion chamber fitted with a gas outlet in which the gas mixture is ignited by an ignition device. To provide a fast-reacting ignition device and generate a controllable flow of pressurized gas at a relatively low temperature, the container is mainly filled with a pressurized inert gas and contains 0.1 to 2.0% vol. of a hydrocarbon and 0.5 to 10% vol. of a gaseous oxidizing agent. On being actuated, the ignition device opens the container closure, ignites the gas mixture flowing into the combustion chamber and maintains combustion by the continuous supply of energy.

Abstract: The subjects of this patent are three amine azide monopropellants, dimethylaminoethylazide (DMAZ), pyrollidinylethylazide (PYAZ) and diethylaminoethylazide (DEAZ). Amine azides decompose on an iridium catalyst at 400° F. and have very low freezing points (<−65° F.). Dimethylaminoethylazide (DMAZ) has been tested and is a suitable replacement for hydrazine in monopropellant thruster applications. An amine azide can be used as a non-carcinogenic alternative for any monopropellant system using hydrazine. An amine azide could be used to replace hydrazine in thrust vector control or reactive control applications for space based applications. An amine azide could be used to replace hydrazine in divert attitude control systems in interceptor missile systems. In a gel fuel formulation the tertiary amine azide gel can have 0.5%-10% gellant. The gellant can be silicon dioxide, clay, carbon or any polymeric gellant.

Abstract: Liquid propellants for the purpose of generating hot gases are described, which propellants comprise solution of a dinitramide compound and a fuel, and are especially suited for space applications, and exhibit the following properties exhibit the following properties: low toxicity; no toxic or combustible vapors; high theoretical specific impulse (as compared to hydrazine); high density (as compared to hydrazine); easily ignitable; storable at a temperature between +10° C. and +50° C.; low sensitivity.

Abstract: Batch-mode and continuous-mode decomposition of nitrous oxide is used to provide multiple ignitions of a solid-propellant gas generator and subsequently control its output gas temperature and flow rate, respectively. To reignite the solid-propellant gas generator, a controlled mass of a reactive oxidizer, such as hot nitrous oxide decomposition products, is injected into the gas generator chamber.

Abstract: Provided is a method for preparing a flowable solid propellant wherein a) liquid oxidizer is added to a tank, b) pellets of cross-linked hydrogel polymer are added to the liquid oxidizer in the tank so that liquid oxidizer is absorbed into the pellets to form flowable combustible pellets and c) the combustible pellets are then flowed into a combustion chamber of a vehicle to combust and the combustion products flow out the propulsion nozzle of the vehicle. Also provided are the liquid oxidizer absorbed flowable combustible pellets so made.

Abstract: An inflator (14) for inflating an inflatable vehicle occupant protection device (12) comprises a pressurized container (20), a gas generating material stored under pressure in the container (20), and an igniter (36) for igniting the gas generating material in the container. The gas generating material comprises an oxidizer and a fuel. At least a major portion of the oxidizer is nitrous oxide in a liquid-gas state. At least a major portion of the fuel is polyvinyl alcohol in a porous, molded solid state (64). A portion of the liquid nitrous oxide is absorbed into the pores of the molded polyvinyl alcohol (64). The gas generating material upon combustion produces a combustion product consisting essentially of carbon dioxide, nitrogen, and water.

Abstract: An inflator apparatus and a method are provided using a quantity of a compensatory material to supplement a stored pressurized gas.

Abstract: A liquid gas generator system supplies gas pressure only when it is needed. Hydrazine and hydrazine blends have been considered for liquid gas generators because of their ability to decompose at ambient conditions on an iridium catalyst to form warm (1000° F. to 1500° F.) gases. Hydrazine is undesirable because of its toxicity and high melting point (34° F.). The tertiary amine azides, which are defined hereinabove and below, are non-carcinogenic alternatives to hydrazine in liquid or gel gas generator systems. These tertiary amines azides are non-carcinogenic alternatives for use with a thermal reactor bed where exothermic reaction releases enough heat to sustain decomposition for furnishing gases for gas generator systems employed. A tertiary amine typically has three hydrocarbons moieties attached to the nitrogen atom. The tertiary amine azides of this invention can have no more than seven carbon atoms in the molecules.

Abstract: This invention relates to liquid propellant compositions containing an enetic material of organic nitrate esters. The organic nitrate esters of the present invention are complexed with a nitrate ester plasticizer, bismuth subsalicylate, and stabilizer to form liquid compositions with an appropriate energy, stability, and sensitivity that is useful as a propellant.

Abstract: Inhibited Red Fuming Nitric Acid (IRFNA) type IIIB and monomethyl hydrazine (MMH) ignite when contacted with each other because of a hypergolic chemical reaction and are the preferred oxidizer and fuel for bipropellant rocket propulsion systems. These propellants can deliver a specific impulse of 284 lbf sec/Ibm and density impulse of 13.36 lbf sec/cubic inch when the engine operating pressure is 2000 psi. Special precautions must be used when handling because of its toxic properties. A fuel gel propellant fuel that would be a suitable replacement for MMH must be less toxic and have a competitive density impulse for the same engine operating conditions. Three compounds meeting the specified requirements have been synthesized and their physical and ballistic properties are evaluated herein as shown in Table 1. The chemical names for these compounds are dimethylaminoethylazide (DMAZ), pyrollidinylethylazide (PYAZ), and bis (ethyl azide)methylamine (BAZ).

Abstract: The non-toxic bipropellent of the present invention contains a non-toxic ergolic miscible fuel (NHMF) and a rocket grade hydrogen peroxide. This non-toxic hypergolic miscible fuel (NHMF) has rapid ignition capability. The non-toxic hypergolic miscible fuel (NHMF) contains 3 species. Namely, a polar organic species miscible with hydrogen peroxide, a propagator, which may be substituted or unsubstituted amines, amides or diamines, and an inorganic metal salt, which reacts to form a catalyst in solution or as a colloid. The inorganic metal salt is miscible with the polar organic species and the propagator in solution. The catalyst has a faster rate of reaction with said rocket grade hydrogen peroxide than the propagator, the propagator has a faster rate of reaction with the rocket grade hydrogen peroxide than the polar organic species, and the polar organic species, propagator and catalyst are mutually soluble.

Abstract: A vehicle safety apparatus (10) for use in inflating an inflatable vehicle occupant protection device (12) comprises a pressure vessel (14) for containing a combustible mixture of gases. A combustible mixture (18) of gases is contained within the pressure vessel. The combustible mixture (18) of gases comprises a combustible fuel gas mixture, an oxidizer gas for supporting combustion of the fuel gas mixture, and an inert gas. The fuel gas mixture comprises hydrogen gas and a hydrocarbon gas. The hydrogen gas comprises about 84 to about 96 molar percent of the fuel gas mixture. The hydrocarbon gas comprises about 4 to about 16 molar percent of the fuel gas mixture. An actuatable igniter (12) is provided for igniting the combustible mixture (18) of gases in the pressure vessel (14). Gas is enabled to flow from the pressure vessel (14) into the vehicle occupant protection device (12).

Abstract: A method and assembly for manufacturing and storing a cryogenic monopropellant, such as cryogenic mixtures of liquid methane and liquid oxygen, and the components thereof. A fuel, such as liquid methane, is manufactured and stored safely and effectively without venting any methane vapors. Liquid methane and liquid oxygen are manufactured such that these components are mixed at thermal equilibrium thereby preventing the formation of vapors in the liquid phase. In this manner, the mixture can be safely stored and used.

Abstract: An improved cryogenic propellant which can be utilized as an improved rocket fuel, hypersonic vehicle fuel, aircraft fuel, explosive, or coolant is described.The improved cryogenic propellant is illustrated by a mixture of liquid hydrogen and solid methane. As an example, an approximate 50/50 mixture by weight of liquid hydrogen and solid methane has a mixture density approximately 2.0 times that of liquid hydrogen alone. This increase in density is partially offset by a loss in ISP of about 8 percent, compared to that of liquid hydrogen alone, with oxygen. Broadly speaking, more of the improved fuel must be carried for a given mission to compensate for the loss in ISP. However, this weight penalty is offset by the 200 percent increase in density. Increased fuel density reduces fuel tank weight and drag.

Abstract: A method of preparing chlorine dioxide in a non-aqueous liquid is disclosed. An aqueous solution of chlorine dioxide is mixed and agitated with a non-aqueous liquid. The chlorine dioxide is extracted into the non-aqueous liquid. In a preferred embodiment, an aqueous chlorite solution is added to a quantity of non-aqueous liquid. Acid is added to the aqueous phase to generate chlorine dioxide. The phases are vigorously agitated to extract the chlorine dioxide into the non-aqueous phase. High concentrations of very pure chlorine dioxide are obtainable. In another preferred embodiment, chlorine is prepared in a non-aqueous liquid and is mixed and agitated with an aqueous chlorite solution. Separation of the aqueous and non-aqueous phases provides pure solutions of chlorine dioxide in the non-aqueous liquid. Very pure aqueous solutions of chlorine dioxide are prepared by mixing and agitating non-aqueous solutions of chlorine dioxide with water.

Abstract: A rocket propellant of improved Isp and thrust is provided by modifying a rocket fuel of RP-1 (a kerosene fraction). Such fuel is combined with an oxidizer (e.g. liquid oxygen, LOX) which defines a rocket propellant of the prior art. Such propellant is modified per the invention by addition to or replacement of, the RP-1 with quadricyclane. In another embodiment, quadricyclane is added to n-Hexane as a fuel composition which is then combined with an oxidizer to define a rocket propellant per the invention. The invention thus provides a number of rocket fuels which upon combination with an oxidizer, provides a high energy density propellant, which can permit increases of over 10 wt % in additional payload for rocket launch vehicles.

Abstract: A gas-producing material for a gas generator, particularly, for an inflatable impact cushion for protecting motor vehicle passengers is made up of a combustible liquid gas mixture of one or several short-chain hydrocarbons and nitrogen monoxide. As a result of exothermic action during combustion there is a multifold increase in volume so that no filters which are required for solid matter generators, are necessary.

Abstract: A gas-producing material for a gas generator, particularly for a belt tightener or for an inflatable impact cushion (airbag) to protect motor vehicle occupants, containing a liquefied gas mixture in which the liquefied gas components consist of a mixture of one or more ethers, olefins, ammonia or hydrogen and nitrous oxide (N.sub.2 O).

Abstract: A novel class of energy-generating chemical processes or reactions uses cryogenically Prepared and stored materials exhibiting volcanic ground states having lifetimes exceeding several seconds. Energy generation is provided through activation of cryogenically prepared and stored material characterized by a volcanic ground potential surface in which its lowest rotation-vibration level has a lifetime sufficiently long to permit practical storage and subsequent energy release. Cryogenic preparation and storage provides that the material is kept in these lowest rotation-vibration levels, thereby avoiding thermodynamic population of the higher levels which are short-lived and therefore not suitable for practical use. In one embodiment, the He .sub.2.sup.++ v=0, J=0 level has been found to have a lifetime of 220 minutes making He.sub.2.sup.++ an ideal candidate for a fuel in which laser-induced fragmentation of He.sub.2.sup.++ into He.sup.+ +He.sup.

Abstract: A propellent medium for a barreled weapon with electrically-supported liquid propulsion, especially for chemical-electrical hybrid drives with regenerative propellent medium injection. Organic compounds of a combination of carbon and hydrogen are contemplated in a ratio with one or more reactive groups which, with a good exothermic reaction of the propellent medium (hydrocarbon), will facilitate the dissociation of molecules or atoms of lower molecular mass. Hereby, a propellent medium component can be formed from charged hydrocarbon ring systems including reactive groups.

Abstract: An energetic compound having the structural formulaO--O--N--Nis disclosed. Routes for synthesizing the compound involving the reaction of oxygen atoms in the [.sup.1 D] electronic state with N.sub.2 O are also disclosed. The energetic compound is particularly useful as an oxidant in chemical propulsion systems.

Abstract: A method, apparatus and the fuel therefor for creating a hot gas jet hydrogen peroxide in a maximum aqueous solution of 55% to which is added a burnable substance. The mixture is passed through a permeable mass of catalytic material such as manganese dioxide in the form of granules of natural pyroluside where the hydrogen peroxide is broken down into water and oxygen. The oxygen thus formed is combined with the burnable substance which may be sugar, coal dust, alcohol, gasoline or other common fuels. Water is added to the mixture to insure storage stability of the hydrogen peroxide.

Abstract: A bipropellant gun in which an immiscible hydrocarbon fuel and oxidizer are combined in the gun's combustion chamber just prior to, or simultaneous with, ignition thereof. The oxidizer consists of hydrogen peroxide having a concentration of less than 73 percent by weight. In one embodiment, the oxidizer alone is bulk loaded into the combustion chamber and a powdered solid hydrocarbon fuel is dispersed into the oxidizer by the function of a pyrotechnic igniter. In another embodiment, the oxidizer and a liquid hydrocarbon are emulsified and the emulsion is bulk loaded into the combustion chamber with a pyrotechnic igniter subsequently initiating combustion. In each embodiment, the volume of the combustion chamber exceeds the volume of fuel and oxidizer and provides a void or headspace of compressible gas which limits the rate of pressure rise in the chamber.

Abstract: A new high energy chemical complex is provided formed from metastable hel fixed on ammonia (HE.sub.m NH.sub.3), so that the metastable helium electron is captured so as to be held in the "L" layer of the metastable helium atom.The process for producing the He.sub.m NH.sub.3 complex comprises the following steps: excitation of helium to create metastable helium; deposition of metastable helium on NH.sub.3 to form the complex; and accumulation or condensation of the product.The invention finds a particular application as a propellant in the aerospace field.

Abstract: Hydrogenolysis of a saturated endo-endo dihydronorbornadiene hexacyclic dimer involves the use of a catalytic amount of a Group VIII metal and the presence of hydrogen. The resulting pentacyclic isomers can be used as a diluent for depressing the freezing point of the saturated hexacyclic dimer which is a component of a high density missile fuel.

Abstract: A blasting composition is disclosed having bulk density and hence explosive energy superior to that of conventional ammonium nitrate fuel oil mixtures, e.g. 94% AN, 6% fuel oil mixtures, but of nearly comparable cost. It comprises two major constituents blended together, namely, (1) about 10 to 40% by weight of a water in oil emulsion which includes aqueous solution of a powerful oxidizer salt as the disperse or inner phase and an oil serving to provide oxygen balance as the external or continuous phase, this emulsion being mixed or blended with (2) a mass of essentially solid particulate oxidizer salt in proportions of 60 to 90% of the total. The emulsion, which may be also a slurry, is mixed to partially but not completely fill the pores or interstices in the solid particulate mass, thereby to increase bulk density, part of the spaces being left unfilled to provide aeration and active sites or "hot spots" to facilitate detonation of the composition by standard detonation devices.