60 results about "Monopropellant" patented technology

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.

This invention is a electronic and mechanical system that comprises of several sub-systems which carries out a new method of using different concentrations of self-propelled hydrogen peroxide-based solutions for direct propulsion in engines designed to use only gas pressure as energy or the system may act as a fuel supplement in existing combustion engines, by manipulating existing oil-based fuel engine's sensor signals to give the system the ability to make the engine run much leaner conditions, or inject less fuel while simultaneously injecting varying concentrations of hydrogen peroxide/water/alcohol solution, consequently saving gas by lowering intake temperatures to reduce the occurrence of knock and exploiting this reduction in temperature by reducing the amount of fuel needed by the engine at all engine running ranges. Standard mechanical pump fluid injection is not new and neither is pressurized propellant system designs, but this system becomes vary abstract when analyzing its method of using an essential, non-cryogenic, safe, self-propelled liquid monopropellant, in hydrogen peroxide; one of the best natural heat absorbers, in water, and releasing the potential of the hydrogen peroxide catalytic decomposition affect in a method of controlled decomposition pressurization within a feed-back loop while adding oxygen to combustion, and the water as a supplement to reduce excess heat in an engine. The system uses a self-pressurizing, concentration-monitoring, high purity stainless steel or aluminum peroxide storage tank which when used in conjunction with a metallic screen catalytic feed-back loop provides pressurized hydrogen peroxide-based solution to the injection solenoid, and when the solenoid is open allows pressurized water and oxygen to the injectors and into an engine. This system allows for a non-cryogenic, safe, non-polluting fuel source for many applications which will only produce water and oxygen, when used as hydrogen peroxide/water for a purely pressure engine, or significantly reduces fuel consumption in piggy-backed hybrid configurations using varying concentrations of hydrogen peroxide, water, alcohol and other fuels for use in the supplementation of combustion in existing fossil fuels engines. Retrofitting this system into existing gasoline, diesel and other fossil fuel engines will be very low cost, since it can intercept most of the factory sensor signals and send manipulated signals to the existing factory ECM inputs to allow the system to change the amount of injected standard fuel and adjust for the much lower intake air temperatures and extra oxygen provided by the decomposed hydrogen peroxide solution injection, while significantly reducing factory fuel system consumption the entire time that the system is actually injecting solution. No system developed has brought the benefits of all of these elements together in this manner. The level of sophistication and methods at which this system regulates itself, manipulates external fuel systems, decomposes hydrogen peroxide solutions into water and oxygen for self-pressurizing the system, and brings these elements together in a synergistic alliance with each other, all while injecting a precise amount of pressurized water and oxygen supplement to combustion events in an engine, are the truly abstract concepts behind this system. Combined with the system's easy adaptability and upgradeability should give a complete insight into the truly abstract design and methodology of this system.

A high energy propellant, comprising an oxetane thermoplastic elastomer energetic binder admixed with a high energy explosive filler. The oxetane thermoplastic elastomer energetic binder preferably comprises from about five percent to about thirty percent by weight and the high energy explosive filler comprises from about seventy percent to about ninety-five percent by weight of the composition. A preferred propellant further includes an explosive plasticizer, preferably in an amount of about four percent to about seven percent of the plasticizer by weight of the propellant. The preferred filler is selected from the group consisting of CL-20, TNAZ, RDX and mixtures thereof. The preferred plasticizer is selected from the group consisting of TNAZ, BTTN, TMETN, TEGDN, BDNPA/F, methyl NENA, ethyl NENA and mixtures thereof. In a preferred embodiment, the propellant is actually a pair of high energy propellants comprising a mixture of first and second high energy propellants with the first propellant having a burning rate at least two times faster than the burning rate of the second propellant. The first propellant includes an oxetane thermoplastic elastomer energetic binder admixed with CL-20 high energy explosive filler. The second propellant including an oxetane thermoplastic elastomer energetic binder admixed with RDX high energy explosive filter. Plasticizers and relative amounts for each of the first and second propellants are the same as for the single propellant.

A single-piston single-unit hydraulic free-piston engine comprises a single-unit fuel pot, a fuel controlling electromagnetic valve, a catalyze bed, a single-piston hydraulic free-piston engine and an electric-control unit. The invention uses high-density hydrogen dioxide or the mixture of hydrogen dioxide and diesel as fuel, and decomposes the fuel via catalysis and decomposition into high-temperature high-pressure mixture gas to drive the single-piston single-unit hydraulic free-piston engine, to exchange the chemical energy of fuel with the hydraulic energy. The invention has high reliability, small volume, low weight and high energy density, or the like, while it can output power in large range by changing the size of engine or the work-frequency of engine. The invention can be used to supply hydraulic energy in non-oxygen condition or oxygen-lack condition.

The present invention relates to a reactor for the decomposition of ammonium dinitramide-based liquid monopropellants into hot, combustible gases for combustion in a combustion chamber, and more particularly a rocket engine or thruster comprising such reactor and a combustion chamber. The invention also relates to a process for the decompostion of ammonium dinitramide-based liquid monopropellants.

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.

The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and hydrogen peroxide, respectively.

A direct-injection swing single-unit engine comprises a single-unit fuel pot, a swing engine, two fuel control electromagnetic valves, two catalysis beds and an electric controller. The invention uses the mixture of high-density hydrogen dioxide and diesel as the single-unit fuel, to be decomposed into high-temperature high-pressure mixture gas via catalysis decomposition, to drive the swing engine, to output swing power directly or output electricity via the generator. The electric controller can control two fuel control valves to switch the frequency to control the swing frequency of the engine or the frequency of output alternative-current. The invention has small volume, low weight, high energy density, and wide application, to be used to supply energy in non-oxygen condition or oxygen-lack condition.

The invention provides a micro swing type monopropellant engine, which comprises a fuel tank, an electronic control unit, a catalytic device, a swing type engine, a fuel distributing valve, a gas exhausting check valve and a muffler, wherein a hydrogen peroxide solution of high concentration is used as a fuel, the electronic control unit controls the fuel flow valve to provide the fuel to the specified catalytic device, high temperature and high pressure gas is generated by decomposing the fuel through catalytic reaction and acts upon a central swing of the swing type engine, so that direct output or electric energy output of swing power is realized. The micro swing type monopropellant engine provided by the invention has the advantages of high integration of work modes, simple structure, convenience in control, high energy density and the like and is applicable to energy supply devices in various anoxic or oxygen-free environments such as outer space, polar regions, plateaus, drilling platforms or underwater.

The invention relates to a micro-flow green high-energy monopropellant thruster structure. The catalytic decomposition of a propellant is realized under the action of a catalyst in a catalysis bed, and the propellant is further combusted in a combustion chamber and then is sprayed out by a spray pipe to generate thrust; and a heat control assembly is installed on the catalysis bed in a thrust chamber, and temperature control and monitoring are carried out on the catalysis bed. The micro-flow green high-energy mono propellant thruster structure has the advantages that the temperature of a capillary pipe is regulated and controlled through a heat conduction sheet, a capillary pipe heat conduction wire and the like, the two-phase flow, generated in the capillary pipe, of the propellant is inhibited under the micro-flow, and the stable operation of a micro-flow green high-energy monopropellant thruster is realized. The micro-flow green high-energy monopropellant thrust has the characteristics of being high in specific impulse, green, non-toxic, light in mass, capable of being pre-packaged and the like, the required force or torque is provided for maneuvering, fast response and the likeof a micro-nano satellite, and the application space of the micro-nano satellite is greatly expanded.

The subject invention relates to oxidizer-rich liquid monopropellants based on ADN or HAN for a dual mode bipropellant chemical rocket engine. Such engines may be part of propulsion systems to be used in aerospace applications for 1) orbit raising, orbit manoeuvres and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes.

The present invention relates to a reactor for the decomposition of ammonium dinitramide-based liquid monopropellants into hot, combustible gases for combustion in a combustion chamber, and a rocket engine or thruster comprising such reactor, wherein the reactor comprises a heat bed exhibiting catalytic activity.