Abstract: A device is disclosed for controlling a rate of gas pressure increase generated by a propellant for propelling a projectile from an upstream towards a downstream end of a gun barrel. The device includes a first surface area defined by the propellant and a deterrent applied to a second surface area defined by the first surface area, the second surface area being less than the first surface area. The arrangement is such that the second surface area defines a deterrent free third surface area of the propellant. A primer is operatively disposed relative to the third surface area such that when the primer is activated, the third surface area of the propellant is ignited. The arrangement is such that firstly, while the third surface area is burning and generating gas between the upstream end of the gun barrel and the projectile, the rate of gas pressure increase begins to propel the projectile towards the downstream end of the gun barrel.

Abstract: There is provided a heat source for a smoking article, including an upstream end and an opposed downstream end, and further including a combustible carbonaceous core and an integral, non-combustible, thermally insulating, peripheral layer. The core extends from the upstream end of the heat source the downstream end of the heat source. The peripheral layer extends from the upstream end of the heat source only part way along the length of the heat source and circumscribes an upstream portion of the core.

Abstract: A device is disclosed for controlling a rate of gas pressure increase generated by a propellant for propelling a projectile from an upstream towards a downstream end of a gun barrel. The device includes a first surface area defined by the propellant and a deterrent applied to a second surface area defined by the first surface area, the second surface area being less than the first surface area. The arrangement is such that the second surface area defines a deterrent free third surface area of the propellant. A primer is operatively disposed relative to the third surface area such that when the primer is activated, the third surface area of the propellant is ignited. The arrangement is such that firstly, while the third surface area is burning and generating gas between the upstream end of the gun barrel and the projectile, the rate of gas pressure increase begins to propel the projectile towards the downstream end of the gun barrel.

Abstract: The invention relates generally to burn rate modifiers and propellants comprising a burn rate modifier. The invention also relates to methods of producing a propellant comprising a burn rate modifier as well as an ammunition cartridge comprising the propellant. The burn rate modifier comprises a compound of formula 1 and the propellant comprises a compound of formula 1 and an energetic material.

Abstract: A method for producing propellant charges with progressive combustion characteristic and a higher charge density than previously considered possible to achieve, intended in the first instance for direct-firing barrel weapons such as tank cannons. Combined in the charge are at least two radially perforated propellant tubes, which are arranged in their entirety inside or after one another, and which have at an e-dimension selected in relation to the actual type of propellant and its desired combustion characteristic, combustion or ignition channels, and which have circular outer and inner boundary surfaces, in conjunction with which, before initiation of the charge, at least one of the total number of outer surfaces of these propellant tubes that are available for initiation has been treated with an inhibition, surface treatment or surface intended to delay the propagation of ignition to that surface so that the combustion of the propellant tubes is partially mutually overlapping.

Abstract: The resent invention relates to a method for producing propellant charges with progressive combustion characteristic and a higher charge density than previously considered possible to achieve, intended in the first instance for direct-firing barrel weapons such as tank cannons.

Abstract: The resent invention relates to a method for producing propellant charges with progressive combustion characteristic and a higher charge density than previously considered possible to achieve, intended in the first instance for direct-firing barrel weapons such as tank cannons.

Abstract: A flexible inflator for an inflation assembly and related gas generating propellant compositions are provided. The flexible inflator includes at least one elongated strand of a propellant co-extruded with a moisture barrier. The propellant compositions are adapted for co-extrusion with a plastic sheath which forms the moisture barrier surrounding the propellant and include a binder fuel component effective to render the composition flexible and to impart sufficient adhesive properties such that the propellant composition and the plastic sheath adhere together, and an oxidizer.

Abstract: A gas-generator is disclosed to intensify output of oil, gas, including gas from coal formations, or metals extracted by underground leaching by breakage and thermo gas chemical treatment of the critical formation zone with gaseous combustion products from a solid propellant. The rate of increase of gas pressure is raised and the effect on the formation is enhanced by assembling the gas generator using coated and bare charges in a selected ratio. The charges burn radially, so the coated charges, which burn only from the center outwards, burn for longer and with a rising output. A two-peaked pressure characteristic is thus obtained. A high-velocity igniter may also be used to give a third, early pressure peak.

Abstract: A method and an apparatus are devised to install an insulation rubber loop in the aft end of a rocket motor case. The method includes the making of a rubber strip into a rubber loop by casting. The rubber loop is partially cured and is then adhered to the inner wall of the aft end of the rocket motor case by using a silicone rubber loop of the apparatus. The silicone rubber loop is caused to deform so as to press against the insulation rubber loop, which is thus securely attached to the inner wall of the aft end of the rocket motor case. The attachment of the rubber loop is further enhanced by heating the rocket motor case to provide heat which is intended to facilitate the curing of the rubber loop.

Abstract: Technology for in situ remediation of undetonated explosive material. An explosive apparatus contains an explosive material in close proximity with a carrier containing microorganisms. An explosive mixture capable of self remediation includes an explosive material that is intermixed with or lies proximate to the carrier. The microorganisms are either mobile or temporarily deactivated by freeze drying until rehydrated and remobilized. The microorganisms are capable of metabolizing the explosive material. Examples of such microorganisms include Pseudomonas spp., Escherichia spp., Morganella spp., Rhodococcus spp., Comamonas spp., and denitrifying microorganisms. If the explosive material fails to detonate, the explosive is remediated by the action of the microorganisms. Remediation includes both disabling of the explosive material and detoxification of the resulting chemical compositions.

Abstract: An oxidizer package for a propellant system for a motor in which the oxidizer is separated from fuel grain, the oxidizer package comprising oxidizer material and an ignition system therefor in a wrapping or sealing material. A hybrid rocket comprising oxidizer material and fuel grain, the oxidizer material being separated from the fuel grain and being in the form of a single package or plurality of packages of oxidizer material and an ignition system therefor, said packages generally conforming to the shape of the rocket. A grid of a pyrotechnic material. A propulsion system for a hybrid rocket comprising oxidizer material in a matrix, mesh, wool, foamed metal or wires of structural or pyrotechnic material.

Abstract: A main energetic ingredient filler useful for propellant-based munitions, comprising filler particles having a fine particle size of less than about 10 micrometers diameter and a thin coating of graphite on the filler particles in an amount such that the weight of the graphite is less than about two percent of the weight of the filler particles. Preferred filler particles have a fine particle size of less than about ten micrometers diameter, and most preferred are fillers with a particle size having an average particle diameter ranging from about two to about eight micrometers. The preferred filler is selected from the group consisting of CL-20, TNAZ, NQ, RDX, HMX and mixtures thereof. Most preferred is a filler of CL-20 ground to an average particle diameter of about five to ten micrometers. The preferred amount of graphite comprises about one percent by weight of the filler particles. The filler may be formed into a propellant including a binder and a plasticizer.

Abstract: An explosive charge such as a cast booster charge (10, 110, 210) includes an explosive charge (14, 114, 214) having a first explosive matrix material (114a, 214a) with discrete bodies (118, 218) of a second material embedded therein. In some embodiments, discrete bodies may comprise explosive material and the first explosive matrix material (114a, 214a) may be more sensitive to initiation than the explosive material of the discrete bodies (118, 218). In a separate aspect of the invention, the discrete bodies may have a minimum dimension of at least 1 millimeter or, optionally, 1.6 millimeter, regardless of the explosive properties of the material therein. In a particular embodiment, discrete bodies may be shaped as cylindrical pellets rounded at at least one end. The cast booster charge (10, 110, 210) may be produced by melting the first explosive, disposing discrete bodies therein and cooling the molten material to solid form.

Abstract: A gas generant material body in the form of a tablet having a triangular cross section and associated methods of gas generation are provided.

Abstract: A towing rocket motor assembly has a tubular solid propellant grain defined by exterior surface area and interior surface area. The exterior surface area is inhibited from ignition within a tubular region of a housing. The housing includes a first end and a second end at either end of the tubular region. The first end defines a plenum having an annular region defined by a diameter larger than that of the tubular region. A plurality of holes formed in the first end communicate with the annular region and are directed substantially in the direction of the second end of the housing. A burn-inhibiting baffle is fitted in the propellant grain wherein an annular spacing is defined between the baffle and the interior surface area of the propellant grain. An ignition assembly, mounted at the second end of the housing, is coupled to the interior surface area of the propellant grain so that the propellant grain burns from the inside out upon ignition.

Abstract: The present invention relates to the field of hybrid gas generators intended to inflate a protective airbag. The generator (1) consists of two metal tubes (50, 51) welded together, the upstream tube (50) being of one piece with an internal partition (26) that has a central orifice (27) closed by a diaphragm (28). The generator thus has a reservoir chamber (29) containing a pressurized gas and a combustion and mixing chamber (46) containing a pyrotechnic device (4) and a support piece (30) carrying a piston-pillar (31) the stroke of which is limited. The hot gases cannot enter the reservoir chamber (29) which may thus contain a greater amount of gas.

Abstract: A propellant cutting assembly and method of using the assembly to cut samples of solid propellant in a repeatable and consistent manner is disclosed. The cutting assembly utilizes two parallel extension beams which are shorter than the diameter of a central bore of an annular solid propellant grain and can be loaded into the central bore. The assembly is equipped with retaining heads at its respective ends and an adjustment mechanism to position and wedge the assembly within the central bore. One end of the assembly is equipped with a cutting blade apparatus which can be extended beyond the end of the extension beams to cut into the solid propellant.

Abstract: A rocket motor having a desensitizing mechanism for preventing explosion or violent reaction during slow cook-off is provided. The rocket motor includes a case contained rocket propellant with a desensitizing assembly attached forward of the propellant charge. The desensitizing assembly is formed with an enclosure containing a desensitizing fluid, and connected to the interior of the rocket motor by a tube which is sealed by a heat sensitive plug. The heat sensitive plug melts at a temperature below the slow cook-off temperature of the rocket propellant. The melting of the plug allows the desensitizing fluid to be ejected into the interior of the casing and onto the propellant charges, thereby, desensitizing the propellant charge.

Abstract: This invention relates to explosive charges in which the chemical and physical composition changes gradually from point to point in order to accomplish differing, specific design objectives. More specifically, the invention relates to an explosive comprised by uniformly mixing components of differing chemical and physical properties in order to take advantage of the functions performed by these different components resulting in an explosive capable of performing multiple or specific tasks.

Abstract: Propellant compositions are coated with an energetic deterrent coating which reduces the burning rate at the surface of the propellant grain and causes the propellant to burn progressively. The use of energetic materials, that are slightly soluble in the coating solvent, improve the burning properties of the propellant without decreasing the chemical energy.

Abstract: A flashless rocket propellent has a continuous potassium sulfate rod extending though the length of the propellent component. The flashless rocket propellent is particularly useful in the MK 66 Rocket Motor.

Abstract: A formulation is provided which is capable of performing as a liner layer between a rocket motor casing and the propellant grain disposed within the interior of the rocket motor casing. The composition produces relatively little smoke during the operation of the rocket motor and is capable of securely bonding a wide range of conventional propellants to a wide range of conventional casings. In one preferred formulation, the liner consists of from from about 50% to about 75% oxygen containing polymer; from about 3% to about 15% curing agent; from about 5% to about 50% filler and from about 0.01% to about 0.5% cure catalyst.

Abstract: A combustion inhibiting composition for use in conjunction with a solid, gas-generating charge, the composition comprising an organic polymeric material containing an oxygen-containing organic filler compatible with said polymeric material, the oxygen to carbon atom ratio of the composition being at least 1:3.

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: The invention provides a method and apparatus (10) for loading a sensitized flowable explosive into a borehole. The apparatus (10) is portable and comprises containers 14, 16 which are pressurizable, for containing an explosive under pressure. Containers 14, 16 have closeable explosive inlets, closeable explosive outlets, and closable fluid inlets. In accordance with the method gas bubbles are dispersed into an explosive base to provide a sensitized explosive which is fed as a batch into the portable containers. The containers are pressurized to de-sensitize the explosive, after which the containers are conveyed to a borehole where the explosive is loaded from the apparatus into the borehole.

Abstract: This invention relates to gas-generative compositions consisting essentially of ammonium perchlorate with a chlorine scavenger, such as strontium nitrate, barium nitrate, potassium nitrate, or lithium carbonate, the combination being present in an amount of about 30 to about 95% by weight, up to about 5% by weight of a binder, up to about 5% by weight of a burning rate catalyst, together with an organic fuel, such as guanidine nitrate. The fuel is in an amount complementary to the combined weight of ammonium perchlorate, burning rate catalyst, chlorine scavenger, and binder, at an oxidation ratio of 0.90 to 0.98. The invention also includes the method of inflating an inflatable device by generating gas employing the noted composition and a gas generator in which the gas-generative composition is that of the present invention.

Abstract: In a gas generant composition containing a source of ammonia, such as an ammonium salt or an ammonia-transitional metal complex that emits ammonia as a degradation product, a zeolite, particularly chabazite, is added as an ammonia-absorbing material. In gas generant formulations containing a copper compound and a nitrate source, the zeolite acts to reduce or prevent formation of copper tetrammine dinitrate.

Abstract: Structure, composition and method in which a fiber reinforcement is impregnated with an interpenetrating network of a light cure resin and a thermosetting resin which are independently curable, enabling autobody component repair, electronic assembly bonding, etc. by selective cure first of one or the other resin, and the support against fluid flow of the uncured resin by the first cured resin.

Abstract: There is disclosed a propellent having a deterred burn rate. The propellent is a particulate containing an energetic binder base and a thermoplastic burn deterrent. The energetic binder has in impetus (energy) in excess of 200,000 foot pounds per pound (mass) and the thermoplastic burn deterrent is both a solid at room temperature and soluble in an organic solvent. The burn deterrent is gradationally dispersed within the particulate with the greatest concentration of burn deterrent at the particulate periphery.

Abstract: A pyrotechnic grain or body of a gas generant having a consolidated or pressed-on, particulate inert burn inhibitor layer thereon. The inhibitor may be a metal oxide, metal sulfide, silica, silicate compound or mixtures thereof. The metal oxide is preferably iron oxide. The metal sulfide is preferably molybdenum disulfide. The preferred inhibitor is a silicate compound, most preferably bentonite. The inhibitor layer most preferably covers only one face or side of the generant body, though it may cover both faces or less than the entire area of one or both faces. The generant may be any conventional formulation which generates nitrogen-containing gas, preferably an azide, and most preferably sodium azide. The generant body may be any shape, preferably a washer-shaped disc. An automotive gas bag inflator may contain a plurality of the composite, inhibited generant bodies, preferably a stack or side by side assembly of such composite, inhibited wafers.

Abstract: A hybrid inflator for an automotive inflatable safety system is disclosed. In one embodiment, a mixture of an inert gas (e.g., argon) and oxygen are contained within the inflator housing and a hybrid propellant (i.e., ballistic properties similar to double-base and long-term stability similar to LOVA) is included in the gas generator.

Abstract: A single charge pyrotechnic material comprising a metal fuel, an oxidizer and a secondary fuel which can be used to control the rate of reaction of the pyrotechnic. The composition can be used as a single charge igniter in an automotive air bag system in place of the separate ignition charge and enhancer charge currently utilized.

Abstract: A gas generant charge comprises a heterogeneous mixture of between about 80 and about 95 wt % of a first gas generant composition 1) and between about 5 and about 20 wt % of a second gas generant composition 2), based on the total weight of 1) plus 2). The first gas generant composition 1) comprises between about 20 and about 40 wt % fuel A) and between about 20 and about 60 wt % oxidizer B). Between about 50 and about 85 wt % of the fuel A) is a triazole or tetrazole compound A.sup.1), and between about 15 and about 50 wt % of the fuel is, a water-soluble fuel A.sup.2). At least about 20 wt % of the oxidizer B), up to 100%, a transition metal oxide B.sup.1); balance of the oxidizer is selected from the group B.sup.2) consisting of alkali and/or alkaline earth metal nitrates, chlorates or perchlorates.

Abstract: The present invention comprises a gas generating composition for, when ignited, providing inflation fluid for inflating an air bag (16) of a vehicle occupant protection device (12). The composition comprises a cyanamide compound complexed with a transition metal nitrate, and a supplemental oxidizing salt admixed with the complex. A preferred cyanamide is dicyandiamide. A preferred complex is bis(dicyandiamide)copper(I)nitrate.

Abstract: A hybrid inflator for an automotive inflatable safety system is disclosed. In one embodiment, a mixture of an inert gas (e.g., argon) and oxygen are contained within the inflator housing and a hybrid propellant (i.e., ballistic properties similar to double-base and long-term stability similar to LOVA) is included in the gas generator.

Abstract: A hybrid inflator for an automotive inflatable safety system is disclosed. In one embodiment, a mixture of an inert gas (e.g., argon) and oxygen are contained within the inflator housing and a hybrid propellant (i.e., ballistic properties similar to double-base and long-term stability similar to LOVA) is included in the gas generator.

Abstract: A hybrid inflator for an automotive inflatable safety system and method for assembling the same. In one embodiment, a mixture of an inert gas (e.g., argon) and oxygen are contained within the inflator housing and a gun type propellant is used in the gas generator to supply the propellant gases.

Abstract: This invention relates to an air bag inflation gas generator used to inflate air bags such as air bags for impact safety devices, life jackets, rafts, and escape chutes, and particularly to a gas generating agent disposed within the device to generate a combustion gas. This invention is structured by forming spacer projections, to keep adjacent gas generating agent; bodies at certain intervals, on one side of the gas generating agent bodies having a through hole formed in the axial direction.

Abstract: A tubeless cased telescoped ammunition is disclosed. The ammunition is ignited and a sequenced ignition is achieved. The ammunition includes a sealing coating for delaying ignition of the main propellant. A sealing ring may also be used to sequence and delay the ignition.

Abstract: An elongate flexible fuse is provided, preferably by an extrusion process, which consists of an oxidizing agent and a fuel present in quantities which will permit a rate of burning of from 10 seconds/meter to 250 seconds/meter. The oxidizing agent is preferably in finely divided form contained in a combustible matrix of fuel or is admixed with finely divided fuel and both contained in a matrix of different material. The ratio of oxidizing agent to fuel is at least 1:1 by weight.

Abstract: There is disclosed a propellent having a deterred burn rate. The propellent is a particulate containing a nitrocellulose base and a cellulosic thermoplastic deterrent, preferably cellulose acetate butyrate or cellulose acetate propionate. The deterrent is gradationally dispersed within the particulate with the greatest concentration of deterrent at the particulate periphery.

Abstract: In a gas generant composition for automotive airbag inflation, a gas generant composition comprises a fuel and an oxidizer the composition includes a metal oxide or metalloid oxide and a processing aid which is a mixture of mica and a salt of a fatty acid.

Abstract: A linear gas generant to be used in, for example, a gas generator for rapidly launching a flier such as a rocket or for rapidly inflating an air bag in a motor vehicle characterized by disposing a fibrous substance, such as copper, silver, aluminum or carbon, along the axial direction thereof. This linear gas generant can be stably deflagrated under a lower ambient pressure, irrespective of a large specific burning area.Disclosed further is a filter structure for a gas generator to be used in an air bag restraint system, which is produced by winding a continuous high-tensile-strength fiber bundle or yarn at a predetermined pitch around an outer surface of a member (a gas generation member) comprising ignition means and gas generation means actuated by the ignition means. This filter structure attains the reduction in weight of the gas generator.

Abstract: A spontaneous ignition agent for an air bag gas generator with excellent temperature resistance comprises essentially nitrocellulose, an inorganic oxidizing agent, and carbon.

Abstract: A gas-generating module for an airbag utilized in motor vehicles, which includes a gas-generating composition and an igniting composition arranged within a container. The gas-generating composition is presently in the shape of a foil-like layer or coating, or alternatively consists of a granulate, and is constituted from components which are a mixture of a composition which is based on a metal azide and an oxidizing agent; a first binder for the granulation of the composition; a second elastic binder and a rapidly combusting igniting mixture whereby the elastic foil layer is arranged in a casing which is pressure-resistant up to a specified degree and which consists of a relatively gas-tight fabric.

Abstract: The gas generator composition contains sodium azide and an oxidizing agent as major components. This gas generator composition additionally contains 2 to 8% by weight of magnesium aluminate. To produce this composition, sodium azide and the oxidizing agent are admixed to a colloidal silica having a silica concentration of 3 to 15% by weight to form a slurry, followed by granulation and drying of the slurry.

Abstract: A gas generant composition contains as a fuel a mixture of a major portion of a triazole or tetrazole and a minor portion of a water soluble fuel; and an oxidizer component, at least 20 wt % of said oxidizer component being a transition metal oxide, such as CuO.

Abstract: This invention relates to fuels used in explosive, pyrotechnic, gas generating, and propellant compositions. The fuel composition of the present invention comprises the reaction products formed as a result of reacting a transition metal or transition metal compound, preferably ferric nitrate or ferric hydroxide with a reducing sugar. The fuel composition of the present invention is suitable for use in explosive compositions by mixing with an oxidizing agent. The fuel composition of the present invention and explosive compounds derived therefrom exhibit nonfouling and noncorrosive properties when used in firearms, along with greatly reduced residue.

Abstract: A thin film of ignition inhibitor is applied uniformly to a rocket propelt grain which may be large and have a complex shape. The film is applied by condensation and polymerization of a vaporized monomer to which the grain is subjected. The monomer is prepared by thermally cracking the dimer of paraxylylene or a halogenated paraxylylene derivative.