Abstract: The amount of particulate matter that is forced into the passenger compartment of an automobile by the deployment of an air bag as it protects the lives of occupants is reduced by improving the filterability of the combustion products of a composition for generating gas to inflate the bag. The filterability is improved by adding a nucleating agent for alkali metal halide vapors formed during said combustion. Silica, alumina, and graphite are representative of the nucleating agents.

Abstract: A reduction in the emission of infrared radiation by the engine of a jet aircraft can be achieved by employing a low molecular weight monohydric alcohol, having a luminometer number of at least about 200 as at least a portion of the fuel. Additional reduction in emission of infrared radiation can be achieved by passing a low molecular weight monohydric alcohol in indirect heat exchange relationship with the hot exhaust nozzle prior to its introduction to the combustion chamber of the engine.

Abstract: This invention relates to a process for the catalytic decomposition of HAN-based monopropellants using a platinum group or transition metal group catalyst that is preferably a supported metal catalyst and/or wire mesh/expanded metal mesh catalyst for the purpose of generating hot gases. These gases are suitably employed for driving a turbine, vane or piston motor, for rocket propulsion or as a convenient and environmentally acceptable means of disposal of surplus propellants or other waste products containing HAN. The HAN-based propellants have low or substantially no volatility and are safer to use than other monopropellants currently used for rocket propulsion or shaft horsepower auxiliary power units.

Abstract: The present invention relates to a general method for increasing the energy conversion from metal-containing rocket and ramjet propellants. According to the invention, this is achieved by means of combining the combustion of the fuel with exothermic intermetallic alloying reactions between components incorporated in the fuel.The invention also concerns rocket and ramjet propellants formulated in accordance with the abovementioned method.

Abstract: A hybrid rocket motor includes a solid propellant fuel grain component which incorporates fuel strengthening agents or mechanical retention devices. In one embodiment, the hybrid fuel formulation is a modified elastomeric polyurethane reaction product based on a liquid hydroxyl-terminated homopolymer of butadiene. A reinforcing agent is added which increases the tensile and tear strength of the grain by 50%. By so strengthening the grain, separation of the grain during the last portion of the burn is minimized. In a second exemplary embodiment, mechanical web stiffeners are provided in the form of a core configuration about which the fuel grain is cast. The web stiffeners are in the form of an open tetrahexagonal truss structure which mechanically traps and adheres to the fuel and becomes an integral part of the fuel grain geometry. In both embodiments, the integrity of the webs is maintained throughout the burn.

Abstract: Shaped particles, comprising a calcium aluminate cement and at least one oxide of a Group VIII metal M selected from nickel and cobalt, said particles containing 10 to 70% by weight of said Group VIII metal oxide (expressed as the divalent oxide, MO) and having a porosity in the range 25 to 50%, in which at least 30% of the pore volume is in the form of pores of size in the range 15 to 35 nm and less than 40% of the pore volume is in the form of pores of diameter greater than 35 nm. These particles are used to catalytically decompose oxidizing agents including hypohalites.

Abstract: A liquid-solid propulsion system having a tank of liquid oxygen and a high pressure chamber loaded with solid grain fuel with a portion of the liquid oxygen being passed through a heat exchanger to convert the liquid oxygen to gaseous oxygen. The gaseous oxygen is directed to the chamber or solid grain fuel to induce a fuel rich gas burn that is directed to a thrust chamber which also receives liquid oxygen to increase the characteristic velocity of the exhaust and thereby provide the specific impulse of the propulsion system. The gaseous oxygen is also directed to the liquid oxygen tank to pressurize the flow of liquid oxygen from the tank. Valves are interposed to control the flow of liquid and gaseous oxygen to provide the required mixture ratio in the thrust chamber for optimum specific impulse or to terminate the thrust of the propulsion system. A method for providing the liquid-solid propulsion system is also disclosed.

Abstract: An autopyrolyzable solid composition for aerobic propulsion consists essentially of an oxidizing agent, a binder and a crosslinking agent. The oxidizing agent is a nitrated explosive material wherein the amount, by weight, of oxygen atoms fixed to the nitrogen atoms of the nitrate groups exceeds 40 percent relative to the total weight of the molecule. The binder is a polyalkadiene having functional terminal groups, such as --OH or --COOH groups, reactive with the crosslinking agent which can have isocyanate, epoxy or aziridinyl functions.

Abstract: A solid propellant rocket motor casing fabricated from strong filament in a matrix of curable polymer known in the trade as a composite motor casing is protected against permeation therethrough over long periods of time of water vapor from the atmosphere by a thin, lightweight, metal foil barrier comprising a metal foil adhesively backed tape such as aluminum foil tape spirally wrapped over the cylindrical or regular surface areas and by a separate, lightweight, metallic shell or dome having a thickness of 0.005 to 0.008 inches adhesively bonded onto the dome ends of the composite material cased solid propellant rocket motor, each metallic shell or dome being made by the use of a plastic or other destructible mold which is first coated with metal by an ion-vapor deposition process to a thickness of less than 0.

Abstract: A propulsion system which utilizes hydrocarbon and hydrogen fuel, having means for cooling of the combustor liner and throat liner of a rocket casing by endothermic pyrolysis of the hydrocarbon in the presence of hydrogen in the fuel passageway. The hydrogen in the fuel accelerates the rate of endothermic pyrolysis in the fuel passageway which is adjacent to and surrounds the combustor liner and the throat liner. Means is also provided for high heat flux to the combustor liner and throat liner from combustion within the rocket casing so that the temperature of the liners exceeds their thermal limits. By the propulsion system and method, hydrocarbon fuel and hydrogen are passed through the fuel passageway which is adjacent to and surrounds the combustor liner and the throat liner in a rocket casing, and heat from the combustion of fuel and hydrogen in the combustion chamber is provided to the fuel passageway by radiation through the combustor liner and the throat liner.

Abstract: A reinforced split-flap hinge for supporting the unpressurized propellant grain of a rocket motor in a high acceleration environment includes a circular piece of material and an afterwardly spaced first annular piece of material bonded to the convex forward surface of the propellant grain, the material of the circular piece of material and the first annular piece of material being chopped fibers of insulating material in a rubber matrix, with a second annular piece of material bonded to the surface of the circular concave piece of material, the convex forward surface of the propellant grain, and the surface of the first annular piece of material, a third U-shaped annular piece of material having first and second skirts extending aft with a first skirt bonded to the surface of the second annular piece of material, the second and third annular pieces of material being made of fabric reinforced polyisoprene, and a fourth annular piece of insulating material made of powder filled polyisoprene positioned between t

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: 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: A method and design are disclosed for the introduction of ammonia gas into he rocket motor gas environment wherein the ammonia gas functions to suppress the flash signature.The firing and pressurization of a sealed container having suppressant vents results in the rupturing of one or more seals for the container containing clathrate means from which adsorbed liquid or gaseus ammonia is boiled out and discharged and mixed with combustion gases prior to being discharged through the exhaust nozzle of a rocket motor.The design for the container for containing clathrate means include as part of one embodiment a toroidal shaped container for installing within the rocket motor exhaust nozzle wherein the container functions as the throat of the exhaust nozzle of the rocket motor. Other embodiments feature the clathrate means in a sealed container which additionally houses the ignitor means.

Abstract: A method for initiating the decomposition of hydrazine fuels by bringing the fuel into contact with an initiator selected from the group consisting of iodates and periodates of metals from groups IIIB, IVB, VIB, VIIB, VIII, IB, IIB and IVA of the periodic table, ammonium iodate di-iodic acid, and heteropoly acids having iodine as their central atom and their salts.

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

Abstract: Polynorbornene has been found to be an excellent binder for the preparation of solid fuel materials and solid propellants. Mixtures of polynorbornene with liquid fuel materials such as kerosene, gasoline, or the advanced missile and aircraft liquid fuels such as JP-4, JP-5, JP-9, JP-10, RJ-4, and RJ-5, for example, can contain 80% or more of the liquid fuel material and still exist in the form of a tough rubbery polymer which has excellent burning characteristics as a solid fuel for a ramjet. Many of these materials can be tailored to have heats of combustion higher than the state-of-the-art solid ramjet fuel formulations.

Abstract: Incorporation of various flame coolants, particularly ferrous oxalate, cupric oxalate and submicron size Fe.sub.3 O.sub.4 in N,N'-dihydroxyethane diamide containing gas generants results in cooler flame temperature and reduced HCN content. Use of downstream coolants further reduces evolved gas temperature and also further reduces HCN content. Devices incorporating these propellants are useful inflators for many devices such as helicopter flotation bags, cargo pallet soft-landing bags, aircraft escape slides, inflatable life rafts and similar items. They are particularly suitable when these items must be man-rated.

Abstract: A method for reducing radar attenuation caused by the formation of free etrons in the exhaust plume of a combusting high impulse rocket propellant which comprises contacting a microwave attenuation reducing additive having at least one element selected from the group consisting of Groups IIIA, IVA, VB, VIB, VIIB and VIII of the Periodic Table with said high impulse propellant. A novel propellant composition characterized by its combustion of low microwave attenuation properties. A class of additives useful for reducing the microwave attenuation characteristics of high impulse propellants.

Abstract: The addition of copper phthalocyanine to composite solid propellant compositions has been found to substantially reduce the tendency toward combustion instability of the propellant. The invention is particularly useful in connection with smokeless composite propellants employing hydroxy-terminated polybutadiene as a binder.

Abstract: A rocket fuel is formed by mixing a liquid prepolymer of butadiene having carboxyl groups with hexamethylene tetramine or a nitroso derivative thereof, shaping and hardening.

Abstract: In a gas generator system, a process for producing gases from hydrazine type monopropellants by the ignition of said propellants by silver nitrate or a mixture of silver nitrate with copper chromite for the decomposition of said propellants to their gaseous end products.

Abstract: A catalyst bed containing alumina pellets on which an active catalyst metal selected from iridium, nickel, niobium, and molybdenium has been deposited is employed to decompose a compound selected from deuterohydrazine, deuteroammonia, hydrazine, and ammonia to yield ammonia free deuterium and nitrogen or hydrogen and nitrogen at a temperature required for immediate use in a DF or HF laser which uses F atoms as the fuel. The decomposition temperature of the catalyst bed is maintained by a hypergolic reaction produced from reacting a fuel selected from the group consisting of hydrazine, methylhydrazine, 1,2-dimethylhydrazine, and blends of the same with an oxidizer selected from the group consisting of inhibited red fuming nitric acid, dinitrogen tetroxide, chlorine trifluoride, and chlorine pentafluoride. A laser employing ammonia free decomposition products of hydrazine and ammonia produced at a temperature between about 500.degree. C. and 900.degree. C. operates at a higher power output. When NH.sub.

Abstract: 1. A catalyst for hydrazine decomposition consisting essentially of a carrier having a pore volume of at least 0.1 cubic centimeters per gram and a specific surface area, measured in square meters per gram, equal to 195 (C.sub.p + 0.013 + 0.736 V.sub.p) where C.sub.p is the specific heat capacity of the carrier at about 25.degree. C in calories per gram per degree and V.sub.p is the pore volume of the carrier in cubic centimeters per gram and metal of the group consisting of iridium, and mixtures consisting of iridium and ruthenium deposited on said carrier in an amount between 20% and about 40% by weight of the catalyst and distributed through the pores thereof in discrete particles sufficiently separated from each other so that they do not sinter or fuse together when the catalyst is at hydrazine decomposition temperature.

Abstract: This invention relates to the catalytic decomposition of hydrazine, catalysts useful for this decomposition and other reactions, and to reactions in hydrogen atmospheres generally using carbon-containing catalysts.

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: Process involves the continuous production of exo-exo stereoisomer of the hexacyclic dimer of norbornadiene using a three component catalytic system of diethylaluminum chloride, ferric acetylacetonate, and bis(1,2-diphenylphosphino)ethane. Temperature range of reaction is about 100-220.degree. F, and residence time is about 1-10 hours. Process further involves taking a product stream, along with any catalyst and other materials and treating it to deactivate the catalyst; then separating the desired exo-exo dimer by various means at a temperature below about 500.degree. F to avoid decomposition of iron salts. Unreacted norbornadiene in the process is recycled.

Abstract: Process involves the continuous production of endo-endo stereoisomer of the hexacyclic dimer of norbornadiene using a three component catalystic system of diethylaluminum chloride, ferric acetylacetonate and triphenylphosphino. Temperature range of reaction is about 100.degree.-200.degree. F and residence time is about 1-10 hours. Process further involves taking a product stream, along with any catalyst and other materials, and treating it to deactivate the catalyst; then separating the desired endo-endo dimer by various means at a temperature below about 500.degree. F to avoid decomposition of iron salts. Unreacted norbornadiene is recycled.

Abstract: Solid components for hybrid propellants are disclosed, which comprise (1) a solid amine and (2) an organic binder, the binderA. being free of groups which are reactive with respect to the amine,B. being selected fromI. diene binders which may optionally contain functional groups and which can be vulcanized by reaction with sulphur,Ii. binders comprising functional groups which can be cross-linked by an epoxide- or aziridinyl-containing cross-linking agent, andIii. polyurethane binders, andC. being capable of hardening at a temperature lower than the melting point of the amine,The proportion of the binder being more than 15% by weight, based on the solid component.

Abstract: Tetracene, H.sub.2 N.C(:NH).NH.NH.N:N.C(:NH).NH.NH.NO (C.sub.2 H.sub.8 N..10 O), that is pelletized by dead pressing at 10,000-30,000 psia is employed as a preferred gas generant for near-neutral combustion products. The chemical, tetracene, is almost completely nitrogen-containing, and has only negligible amounts of carbon or oxygen which results in producing dominant combustion products of nitrogen. Tetracene is employed as a gas generant in a method which produces near-neutral combustion products that are compatible with a variety of oxidizers (e.g., IRFNA, ClF.sub.3, ClF.sub.5, etc.) and a variety of fuels (e.g., UDMH, MHF, etc.). Contact of the combustion products with the oxidizers or fuels does not interfere with their normal functioning.

Abstract: A process for the rapid production of a substantial volume of non-toxic gas at a moderate temperature, comprises:A. effecting combustion of a pyrotechnic charge consisting of a composite solid propellant having a high content of inorganic oxidant, in excess of 80 percent and a low content of a carbonaceous, non-nitrogenous binder, not in excess of 17 percent in a combustion chamber to produce a substantial volume of combustion gases at an elevated temperatureB. a first cooling phase in which the hot combustion gases are diluted with oxygen obtained by the thermal decomposition of an oxygen-containing inorganic compound which has a low thermal stability and liberates, in gaseous form, only oxygen, whereby the combustion gases are cooled to a temperature of from 225.degree. to 700.degree.C, andC. a second cooling phase in which the gas mixture from the first cooling phase is cooled by contact with cooling means to the temperature of utilization.

Abstract: A rocket motor is described in which a thin layer of metallic foil or the ke is used between a silicone rubber insulator and an isocyanate cured, hydroxy terminated polybutadiene bound propellant grain to prevent migration of isocyanate into the silicone rubber liner.

Abstract: A method of suppressing unstable burning in a solid propellant rocket motor comprising combusting a silicone elastomer with burning of the solid propellant to produce a continuous stream of small silica particles which suppress instability.

Abstract: 1. A solid polyurethane propellant binder composition which comprises a polyurethane composition comprising the reaction product of nitrocellulose plasticized with a plasticizer selected from the group consisting of nitroglycerin and triethyleneglycol dinitrate, an aromatic diisocyanate and a polyol having a molecular weight of about 500 to 3,000 selected from the group consisting of dicarboxylic acid-polyol-polyesters and polyoxyalkylene ethers, and mixtures thereof, wherein said plasticizer is present in the proportion of about 40 to 60 parts by weight per 100 parts by weight of binder composition, wherein said nitrocellulose contains about 11.0 to 13.0% nitrogen and is present in the proportion of about 0.7 to 1.0 part per part of said polyol, and wherein said diisocyanate is present in an amount to provide an NCO/OH ratio of said diisocyanate to said polyol of about 1.2/1 to 3.0/1.

Abstract: Solid ramjet fuels made up of mixture comprising hydroxy terminated polybdiene or the like in combination with other hereinafter specified hydrocarbons are disclosed. When combusted, in the presence of air, the fuels of this invention exhibit combustion efficiencies similar to that of hydroxy terminated polybutadiene alone.

Abstract: A chemical gas generant mixture of carbon, an oxidizer which does not contain hydrogen and, optionally, a carbonate or other coolant.

Abstract: A process for simulating the infrared radiation in wave length and intensity and the spatially extended characteristics of the plumes of turbojet engines comprising burning fuel-rich solid gas generator compositions, comprising an organic binder, an oxidizer, and dispersed inorganic particles, of a character such that venting of the combustion products directly into the atmosphere or venting them into the inadequate plume of a separate gas generator to provide a combined plume, produces a plume having the size and radiating characteristics of the turbojet plume being simulated.

Abstract: A solid boron fuel burning ramjet engine having a cylindrical primary burner located within a ramjet combustion chamber. A portion of the air bypasses the primary burner to provide secondary burning at the outlet of the primary burner. Solid boron fuel pellets are ground to powder in a wire brush fuel mill with the fuel then being carried to the primary burner by air which is passed through the fuel mill.

Abstract: A device for generating gas at a constant rate for raising a water profiler uring measurement of different parameters of the sea. The device is of a specific construction including a housing with end caps. LiH is placed into the housing and capped. A blasting cap ruptures one end cap permitting water to enter the housing. The water mixed with the LiH generates hydrogen gas and LiOH which provides lift for a profiler. A plurality of the gas generators are assembled onto a profiler for causing the profiler to ascend as many times as the number of devices carried by the profiler.

Abstract: In a solid fuel ramjet in which a fluid flow boundary layer extends along a urning fuel grain and receives combustible material liberated from the grain, exciting oscillations in air flowing toward the grain so that oscillations continue in the boundary layer and promote vortices in the layer to mix the air and the combustible material.