705results about "Explosives" patented technology

Heating units, drug supply units and drug delivery articles capable of rapid heating are disclosed. Heating units comprising a substrate and a solid fuel capable of undergoing an exothermic metal oxidation reaction disposed within the substrate are disclosed. Drug supply units and drug delivery articles wherein a solid fuel is configured to heat a substrate to a temperature sufficient to rapidly thermally vaporize a drug disposed thereon are also disclosed.

A chemical reaction between molten aluminum and an oxygen carrier such as water to do useful work is disclosed, and in particular two chemical methods to obtain aluminum in its molten state. One is to detonate a HE/Al mixture with surplus Al in stoichiometry, and the other is to use an oxidizer/Al mixture with surplus Al in stoichiometry. Additionally, there is a physical method of shocking and heating Al using high temperature reaction products. The produced Al in its liquid form is forced to react with an oxygen carrying liquid (e.g. water), giving off heat and releasing hydrogen gas or other gaseous material. A water solution of some oxygen-rich chemicals (e.g. ammonium nitrate) can be advantageously used in place of water. A shaped charge is also disclosed having a liner that contains aluminum, propelled by a high explosive such as RDX or its mixture with aluminum powder. Some aluminum in its molten state is projected into the perforation and forced to react with water that also enters the perforation, creating another explosion, fracturing the crushed zone of the perforation and initializing cracks. Another shaped charge is shown having a liner of energetic material such as a mixture of aluminum powder and a metal oxide. Upon detonation, the collapsed liner carries kinetic and thermal energy. Also shown are methods to build and to detonate or fire explosive devices in an oxygen carrying liquid (e.g. water) to perforate and stimulate a hydrocarbon-bearing formation.

The invention provides shock initiation devices comprising multilayer structures with constituent layers that undergo an exothermic self-propagating reaction once initiated by shock. The multilayer structures may be used as components in shaped charges, EFP devices, warheads, munition casings, interceptors, missiles, bombs, and other systems. The reactive layer materials may be selected based on required structural properties, density and reaction temperature.

An embodiment of the invention includes a method of simulating a behavior of an energy distribution within a soldered or brazed assembly to predict various physical parameters of the assembly. The assembly typically includes a reactive multilayer material. The method comprises the steps of providing an energy evolution equation having an energy source term associated with a self-propagating reaction that originates within the reactive multilayer material. The method also includes the steps of discretizing the energy evolution equation, and determining the behavior of the energy distribution in the assembly by integrating the discretized energy evolution equation using other parameters associated with the assembly.

The compositions of different energetic metallic particles and corresponding coatings are chosen to take advantage of the resulting exothermic alloying reactions when the metals are combined or alloyed through heat activation. Bimetallic particles composed of a core/shell structure of differing metals are chosen such that, upon achieving the melt point for at least one of the metals, a relatively substantial amount of exothermic heat of alloying is liberated. In an embodiment, the core metal is aluminum and the shell metal is nickel. The nickel may be applied to the outer surface of the aluminum particles using an electroless process from a metal salt solution with a reducing agent in an aqueous solution or a solvent media. The aluminum particles may be pretreated with zinc to remove any aluminum oxide. The resulting bimetallic particles may be utilized as an enhanced blast additive by being dispersed within an explosive material.

An engineered composite system designed to be passive or inert under one set of conditions, but becomes active when exposed to a second set of conditions. This system can include a dissolving or disintegrating core, and a surface coating that has higher strength or which only dissolves under certain temperature and pH conditions, or in selected fluids. These reactive materials are useful for oil and gas completions and well stimulation processes, enhanced oil and gas recovery operations, as well as in defensive and mining applications requiring high energy density and good mechanical properties, but which can be stored and used for long periods of time without degradation.

Weapons, weapon components and related methods are provided. In one embodiment a weapon component includes one or more discrete fragments embedded in a reactive material matrix. The weapon component may be used as a warhead that includes an explosive charge. In one embodiment the weapon component is configured such that, upon explosive launch, the reactive material matrix fractures to define one or more reactive material matrix fragments. The weapon component may be configured such that the discrete fragments are propelled at a first velocity over a defined distance while the reactive material matrix fragments are propelled at a second velocity over the defined distance, the second velocity being less than the first velocity. The weapon component may be used, for example, in a countermeasure weapon used to defeat a target weapon. Other embodiments of weapon components, weapons and related methods are also disclosed.

A solid-solid hybrid gas generator composition includes a solid gas generator material and a solid, flame retardant material. The flame retardant material may include one or more bromine-, chlorine- and phosphorous-containing compounds. The gas generator material and flame retardant material may be in the same vessel.

The present invention provides an inflator capable of realizing downsizing and weight reduction. An inflator for an air bag comprising, in a housing having a gas discharging port, a combustion chamber accommodating a molded article of a gas generating composition which is burnt to generate a gas and an ignition means to ignite the molded article of a gas generating composition, wherein the molded article of the gas generating composition contains a metal component and meets the requirement (A) the (theoretical) combustion flame temperature of the molded article of the gas generating composition is 2000° C. or less, and part or the whole of the metal or metal oxide after combustion of the molded article of the gas generating composition has a melting point not lower than the combustion flame temperature, and the requirement (B) bulk combustion residues remain in the combustion chamber at the time of combustion of the molded article of the gas generating composition.

An electrically controlled propellant comprising an ionomer oxidizer polymer binder, an oxidizer mix including at least one oxidizer salt and at least one eutectic material, and a mobile phase comprising at least one ionic liquid is disclosed. The PVAN polymer in the present invention may be of medium (>100,000) to high molecular weight (<1,000,000). The present invention also may include the controlled cross-linking of the polymer using epoxy resins, the use of moisture barrier coating, the addition of an energetic combustion additives such as Chromium III and polyethylene glycol polymer.

The invention, as embodied herein, comprises a new composition that provides different outputs depending upon the level of stimulus supplied to the composition. More specifically, if the composition is subjected to a weak shock, the composition produces fragments that burn upon their surfaces. If the composition is subjected to a strong shock, the bulk of the fragments will initiate, and, depending upon the make-up of the fragments, an explosive, propellant, or pyrotechnic, a different output will result.

A fuel or fuel blendstocks for jet, gas turbine, rocket, and diesel engines, particularly jet and rocket engines utilizing components of conventional petroleum not currently utilized for jet, gas turbine, rocket, and diesel fuels, such as benzene, butanes, butanes, and methyl tert butyl ether (MTBE) alklyated with aromatic moieties to make monoaromatics used in jet and diesel fuels. Additionally, a fuel having such monoaromatics has multiple desired properties such as higher flash point, low pour point, increased density, better lubricity, aerobic degradability, reduction in toxicity, and additionally can deliver benefits in blendstocks.

The invention discloses a production method of an emulsified explosive, which comprises the following steps that: water phase and oil phase are prepared, and then water phase solution is added into oil phase solution to be emulsified by an emulsifier to prepare a latex matrix, and simultaneously a cooling steel strip controls the temperature of the latex matrix to be 90 to 105DEG C; and the matrix is cooled, the cooled latex matrix is added into a sensitizing machine, and then one or two of perlite and chemical blowing agent is added in for sensitization; and then the explosive is charged, and finally the loaded explosive is packaged to prepare the emulsified explosive. The production method of the emulsified explosive has the advantages of reducing the production cost, having no waste explosive, waste material, waste gas, waste water and dust in production, realizing the free switching of a plurality of sensitization methods, such as physical sensitization, chemical sensitization and physical and chemical composite sensitization, so as to meet the needs of different consumers; perlite is adopted for physical sensitization, and can improve the explosion performance and the storage performance; and the production method of the emulsified explosive can adapt to the requirements of small-diameter explosive charging and full-automatic packaging automatic calandria.

A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.

A warming device consisting essentially of a heat generating main body comprising a heat generating element and an air-permeable holding member having the heat generating element enclosed therein. The warming device has a receiving part for receiving a part of a body being inserted. The heat generating element comprises a sheet which contains an oxidizable metal, a moisture-retaining agent, and a fibrous material and is prepared by papermaking.

A reactive munition uses a housing made from a housing in a state that is three-dimensionally rigid. The housing can be made of metal, such as aluminum. A reactive filler, such as powdered polytetrafluoroethylene (PTFE), fills the one or more cavities in the aluminum housing. A jacket encases the housing filled with the reactive filler.

A material for a pyrotechnic composition and related pyrotechnic compositions are provided in which the material includes a substituted basic metal nitrate including a reaction product of an acidic organic compound and a basic metal nitrate. A method for enhancing a burn rate of a gas generant composition and a burn rate enhanced gas generant composition including a reaction product of basic metal nitrate and tetrazoles, tetrazole derivatives, and combinations thereof, and a nitrogen-containing co-fuel such as guanidine nitrate are also disclosed. The burn rate enhance gas generant composition may optionally include an additional oxidizer such as basic copper nitrate.

A solid propellant rocket engine includes: a propellant formed into a predetermined shape having a combustion cavity and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand the hot, high-pressure gas into the atmosphere, where the propellant forms the nozzle as a part of the predetermined shape. A multi-stage rocket unit, a multi-engine rocket stage, and a super-staged rocket each has many rocket engines.

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.

A gas generating process, which is for the continuous production of energy and hydrogen for rocket and other propulsion and is also for the continuous production of hydrogen, utilizes the reaction of metallic materials, particularly aluminum, with organic materials, particularly hydrocarbons provided as jet fuel, and with water or an oxidizer which is predominantly water. In comparison with related reactions, the reaction produces hot gases containing more hydrogen and the products have a lower temperature for the same specific impulse. The process incorporates organic liquids with metallic powders to produce desirable, lower molecular weight exhaust gas products; and the increased hydrogen is desirable for use with a fuel cell and in connection with propulsion of a super-cavitating underwater device. The process is advantageous in that a metal, in powdered form, and a hydrocarbon liquid may be provided together as a slurry or gel for effective metering. The metallic material may also be provided with the organic material in the form of a binder as used in solid propellants, and the organic material and water may be provided together in the form of a water containing liquid monopropellant. The hydrogen containing product gases from the reaction may be further reacted with suitable oxidizers for production of additional energy or steam. The reaction is particularly useful for underwater vehicles where ambient water is available and the reaction products may be used for propulsion.

The present invention is an electrically controlled propellant comprising a binder, an oxidizer, and a cross-linking agent. The boric acid (the cross-linking agent) has been found to function as a cross-linking agent for the high molecular binder used to make the propellant, thereby improving the composition's ability to withstand combustion without melting. The present invention also may include 5-aminotetrazole (5-ATZ) as a stability-enhancing additive. The binder of the present invention may include polyvinylalcohol (PVA) and/or the co-polymer of polyvinylalcohol/polyvinylamine nitrate (PVA/PVAN).

The invention discloses an azotetrazole-based energetic compound with the composition of M(ATZ)(L)n question mark mH2O, wherein, M refers to Mn, Co, Ni, Cu, Zn or Pb; ATZ refers to 5, 5'-azotetrazole ion, L refers to 1, 10-o-phenanthroline or 2, 2'-dipyridyl, n refers to 1 or 2, and m refers to an integer or a decimal between 0 and 10. In the invention, the 1, 10-o-phenanthroline or the 2, 2'-dipyridyl is introduced into the M(ATZ) as an ancillary ligand to obtain a novel compound, thus integrating the characteristics of high efficiency, insensibility and environmental protection of a catalyst on the premise of the combustibility improvement of composite propellants. The azotetrazole-based energetic compound has the advantages of simple preparation method and accessible raw materials.

A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-holding zone igniter (74) is adjacent to and ignites recirculation of at least a portion of the first propellant (69) and at least a portion of the second propellant (71) within a flame-holding zone (76).

The invention relates to an emulsified water in oil composition using a novel additive surfactant package containing a PIBSA-derived surfactant with a molecular weight in the ranged about 300 to 3000 and in the range of about 0.01% to about 10% by weight of the composition and an alkylamine ethoxylated surfactant in the range of about 0.01% to about 10% by weight of the composition.

The present invention discloses an explosion welding method with aluminum-steel composite materials; a double-layer aluminum plate (4) is arranged on a basic level steel plate (6) through a support (5); a buffer protecting layer is paved on the surface of the double-layer aluminum plate; an explosive (2) is placed on the surface of the buffer protecting layer in the way of stage gradient style, so that per unit area explosive capacity is stepped gradually decreased from the center of the double-layer aluminum plate to two ends; a large acreage of the aluminum - steel composite materials is gained through the explosion welding method; per unit area explosive capacity is stepped gradually decreased from the center of the double-layer aluminum plate to two ends; the material of the basic level steel plate is a carbon steel or a low alloy steel; the material of the double-layer aluminum plate is a pure aluminum or an aluminum alloy with less or equal to 0.1 percent of Mg. The explosion welding method of the present invention has the advantages of high intensity and equal strength in composite bonding, no excessive melting, delaminating, or non-compounding phenomenon at an interface, being capable of making thick double-layer aluminum plate composite materials through once explosion welding, convenient in production and higher in efficiency.

A hybrid rocket engine and a method for propelling a rocket utilizing a vortex flow field. The flow field includes an outer fluid vortex spiraling toward a closed end of the flow field generating apparatus and an inner fluid vortex substantially concentric with the outer vortex spiraling away from the closed end and toward an outlet opening in which the inner vortex spirals in the same direction as the outer vortex, but in the opposite axial direction. The invention also relates to a rocket propulsion system utilizing the flow field in which the propulsion system includes a combustion chamber with a fuel source and an oxidizer source that deliver the said fuel and said oxidizer to the said outer and inner vortexes in a manner to support a combustion process while flowing along the flow field.

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.

A poured-type azido high-polymer bonded explosive and a preparation method of same. For solving a problem of low energy of an HTPB-based PBX explosive, an azido polyether energetic binder is added to a formula system of the PBX explosive, and by means of addition of an alkynol compound as a curing additive agent, a curing reaction time of the azido polyether binder system is greatly reduced. By means of addition of a high-energy-density main explosive and a metal fuel component, the obtained poured-type azido PBX explosive has high explosion heat and explosion volume, is higher than 1.80 g/cm<3> in density and is more than 1.60 TNT in power. Meanwhile, the poured-type azido PBX explosive has a low sensitivity level, is higher than 49 J in drop hammer impact energy I50 and is not more than 40% in friction sensitivity.

A prilling method comprising the steps of: providing a molten first component, mixing at least a second component with the molten first component, reacting the components to form a shear-thinnable mixture; and prilling the shear-thinnable mixture wherein the prilling comprises mechanically agitating in the prill head to shear thin the shear-thinnable mixture sufficiently to permit prilling. The inventive method can be used to produce fertilizer product comprising ammonium sulfate nitrate.

The invention relates to novel Methylobacterium species that are capable of degrading nitroaromatic and nitramine compounds. Compositions, kits and methods of using the Methylobacterium species for the degradation of nitroaromatic and nitramine pollutants are provided. More specifically, compositions and methods for the degradation or bioremediation of nitroaromatic and nitramine explosives and explosive residues are provided.