Abstract: Disclosed is a method for forming a catalyst bed for catalytic decomposition of hydrogen peroxide, which uses 3-D printing techniques to form a porous metal backbone and treating the surface of the metal backbone to activate the surface, wherein the metal backbone is formed of a noble metal or a manganese complex. Also disclosed is a rocket engine having a 3D printed catalyst for catalytic decomposition of hydrogen peroxide, a fuel store, an oxidizer store, and a rocket engine, wherein the oxidizer is a stabilized solution of hydrogen peroxide, and a 3D printed catalyst bed.

Abstract: A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer. Combustion of the fuel material in the combustion chamber may generate thrust of no more than 5 N at an oxidizer flow rate of no more than 5 g/s.

Abstract: The present invention relates to a foam material comprising:—a structural matrix (1),—at least one guest phase (2), and—a fluid, the material being characterised in that the structural matrix (1) comprises a plurality of interconnected pores (3), the one or more guest phases (2) are accommodated inside at least one pore (3) of the structural matrix (1) and the fluid is accommodated inside the pores (3). The present invention further relates to the process for preparing the foam material according to the present invention and to the various uses of the foam material according to the present invention.

Abstract: A fuel supply nozzle unit includes a fuel supply nozzle, a rear end and an end plate. The fuel supply nozzle includes a front end that has a plurality of fuel supply holes. The rear end extends from the front end and is formed with a threaded portion on its outer surface. The end plate is connected to the rear end and is formed with a plurality of threaded holes.

Abstract: A reactor for reducing the concentration of NOx in a stream comprising: an inlet for the stream; an outlet for a stream containing a reduced concentration of NOx; one or more catalyst beds comprising a ceramic or metallic foam with a NOx reduction catalyst; one or more flow paths from the inlet to the outlet that passes through at least one catalyst bed wherein the catalyst beds are closed at the top and bottom so that the flow path through the catalyst bed passes through the sides of the catalyst bed in a lateral flow is described.

Abstract: A catalyst bed comprising a ceramic or metallic foam comprising one or more NOx reduction catalysts is described. A method for reducing the concentration of NOx in a dust containing gas stream comprising: a) passing a first gas stream containing NOx into a contacting zone; b) contacting the first gas stream with a ceramic or metallic foam catalyst bed having one or more flow paths through the catalyst bed wherein the ceramic or metallic foam comprises a NOx reduction catalyst to produce a second gas stream with a reduced NOx concentration; and c) passing the second gas stream out of the contacting zone wherein the first gas stream has a dust concentration of at least 5 mg/Nm3 and the pressure drop of the foam catalyst bed increases by 300% or less relative to the initial pressure drop of the foam catalyst bed due to dust accumulation, measured under the same conditions is also described.

Abstract: A catalyst bed comprising a ceramic or metallic foam comprising one or more NOx reduction catalysts is described. Further, a method for reducing the concentration of NOx in a dust containing gas stream comprising: a) passing a first gas stream containing NOx into a contacting zone; b) contacting the first gas stream with a ceramic or metallic foam catalyst bed having one or more flow paths through the catalyst bed wherein the ceramic or metallic foam comprises a NOx reduction catalyst to produce a second gas stream with a reduced NOx concentration; and c) passing the second gas stream out of the contacting zone wherein the first gas stream has a dust concentration of at least 5 mg/Nm3 and the second gas stream comprises at least 50% of the amount of dust in the first gas stream.

Abstract: The present invention relates to a monopropellant system for a regenerative fuel cell (RFC) and a method for mono-propulsion using same and, more specifically, to a monopropellant system for an RFC which can, when operating an electrically propelled airplane adopting an RFC system, secure more energy via a monopropellant than conventional methods and use same as a propulsion source for airplane takeoff and so on, and to a method for mono-propulsion using the monopropellant system for an RFC.

Abstract: Described herein is an apparatus that includes an estimation module that estimates a probability of an ice crystal icing engine event based on infrared satellite data, numerical weather prediction data, and empirical data corresponding with at least one actual ice crystal icing engine event. The apparatus also includes a data product module that generates a data product that indicates the estimation of the probability of an ice crystal icing engine event. Additionally, the apparatus includes an output module that communicates the data product to a recipient.

Abstract: 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.

Abstract: Novel monopropellants are provided. The monopropellants are based on N2O, to their preparation method and their uses for space propulsion.

Abstract: A propulsion system is disclosed that uses metal fuel particles heated to a range from 3000° K. to 6000° K. by reaction with oxygen in air inside a cyclone combustor to form metal oxides that are retained and removed from the combustor for re-conversion to metal, while nitrogen in the air is heated to the temperatures that on supersonic exhaust propels 50,000 ton monohull ships to from 50 to 100 knots. The ship can accelerate by electromagnetic force from a MHD generator-accelerator rendered electrically conducting by alkali metal seed injection into the gas. Also disclosed are 10 MW to 1000 MW Closed Cycle MHD power plants fired by natural gas into a top half of a falling pebble bed heat exchanger that transfers 2000° K. to 3000° K. heat to a noble or diatomic gas in a bottom half of the exchanger that on exit is seeded with an alkali metal rendering the gas conducting.

Abstract: This invention is a packaged propellant air-induced variable thrust rocket engine that has a vast number of uses and applications for this invention. The primary purpose of the device described here is to provide a light weight, torque and vibration free thrust generator for the propulsion of aircraft. This device will facilitate the fabrication of very light weight aircraft because of the lack these forces. This device can also be used anywhere high velocity air flow and or the resulting thrust is needed. The invention uses aerodynamic principles to compress and accelerate the incoming air, prior to it being heated and accelerated by a short duration burst of thermal and kinetic energy from discrete packets of a mixture of oxidizable fuels. The heated and accelerated air then expands as it travels thru the device providing thrust.

Abstract: Methods and systems are provided for propelling a vehicle. In an embodiment, by way of example only, a method includes flowing a decomposed hydroxylammonium nitrite (HAN)-based propellant into a chamber, introducing an aspirated non-polar fuel into the chamber, and combusting the decomposed HAN-based propellant and the aspirated non-polar fuel to produce an exhaust gas.

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: A new rocket motor assembly configuration is disclosed. Amine based oxidizer is decomposed in the presence of a metallic catalyst to generate an oxygen rich hot gas stream. The hot gas stream is used to trigger a Magnesium based solid fuel in the combustion chamber. The thrust of the rocket motor may be regulated at multiple points. This design thus offers an IM compliant, thrust-adjustable rocket motor that is of a low hazard classification without compromising its performance.

Abstract: A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a secondary gaseous fuel is fed into the inlet air port such that the secondary fuel mixes with air, thereby enabling the mixture of the air and the secondary fuel to combust in a catalytic reactor to produce high temperature, oxygen-rich gases that flow into the main combustor chamber. Proper proportional amounts of the two fuels are determined as a function of altitude.

Abstract: A thruster for exo-atmospheric vehicles with electro-thermal thrust augmentation and having internally embedded heating elements for direct contact heating of gaseous products released by a propellant, particularly hydrazine, so as to increase the Specific Impulse (Isp) of the thruster. The electrical heating elements are resistant to hydrazine products. The thruster is configured as a closed sealed chamber divided into a decomposition section upstream and a heating section downstream. At least one heating element is disposed in the heating section, directly in a mixture catalyst forming a porous bed, or within a concentric ceramic tube operative as a heat exchanger, to heat the gaseous products by direct contact. The heater indirectly heats the catalyst in the decomposition section and directly heats the heating section. The thruster is operable both in space and at sea-level gravity and barometric pressure.

Abstract: An engine for creating a propulsive force includes turbomachinery for generating a flow of hot exhaust gases and an initial thrust force, an augmentor positioned aft of the turbomachinery, and a system for injecting an oxidizer, which preferably undergoes thermal decomposition, into the hot exhaust gases so as to significantly increase the thrust force generated by the engine. In a preferred embodiment of the present invention, the oxidizer comprises liquid high test peroxide.

Abstract: An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and decomposition products of the ionic salt.

Abstract: A method for designing and assembling a high performance catalyst bed gas generator for use in decomposing propellants, particularly hydrogen peroxide propellants, for use in target, space, and on-orbit propulsion systems and low-emission terrestrial power and gas generation. The gas generator utilizes a sectioned catalyst bed system, and incorporates a robust, high temperature mixed metal oxide catalyst. The gas generator requires no special preheat apparatus or special sequencing to meet start-up requirements, enabling a fast overall response time. The high performance catalyst bed gas generator system has consistently demonstrated high decomposition efficiency, extremely low decomposition roughness, and long operating life on multiple test articles.

Abstract: An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and decomposition products of the ionic salt.

Abstract: A hypergolic fuel system comprises hydrogen peroxide, silane and a liquid fuel. The hypergolic fuel system is employed in a method for producing thrust, for example in a rocket, by contacting hydrogen peroxide with silane to obtain initial ignition and thereafter feeding a liquid fuel for combustion.

Abstract: A micro air vehicle is propelled by a bipropellant micro engine supplied with hydrogen peroxide and a hydrocarbon fuel. The hydrogen peroxide is decomposed to produce steam and oxygen at high temperature and the hydrocarbon fuel is burnt within a combustion chamber with oxygen produced from such decomposition. Products of such decomposition and combustion are exited through a nozzle to produce thrust. In a preferred embodiment there is also a ducted turbofan located downstream of the nozzle exit.

Abstract: 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.

Abstract: A process for the production of a transverse thrust in a flying object in which a defined quantity of a monergol propellent substance is introduced into a propulsion unit, which is arranged transversely relative to a longitudinal axis of the flying object to produce a thrust transverse to the longitudinal axis of the flying object. The propulsion unit has a combustion chamber, a supersonic nozzle connected to the combustion chamber and a source of heat to combust the propellant substance and produce the desired thrust for a prescribed time.

Abstract: A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20′) in a turbopump fed rocket engine (12′). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentrations of hydrogen peroxide into the pre-burner (50); (c) converting the fuel and hydrogen peroxide into a fuel rich gas; and (d) passing the fuel rich gas through a turbine (20′), thereby using high concentrations of hydrogen peroxide to drive the turbine. Thus, by utilizing a fuel rich pre-burner (50) that operates at a very low mixture ratio, the drive gas for a turbine (20′) can be maintained at moderate temperature levels.

Abstract: A gas generator, comprising a catalyst section and a mixer section. The catalyst section has openings through which a material enters and reacts with a catalyst to decompose and to produce heat. The mixer section, located downstream of the catalyst section, introduces an additional amount of the material. The heat produced in the catalyst section is sufficient to decompose the additional amount of material introduce into the mixer section without exposure to said catalyst. The catalyst bed assembly could be part of a turbopump assembly. A nozzle downstream of the mixer section directs the exhaust towards a turbine. The turbine drives a pump. The amount of material added to the mixer is selected to produce a desired amount mass flow through the nozzle. Adding material to the mixer causes the turbopump to supply more fuel or oxidizer to a rocket engine. Thus, the rocket engine is throttleable.

Abstract: A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20′) in a turbopump fed rocket engine (12′). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentrations of hydrogen peroxide into the pre-burner (50); (c) converting the fuel and hydrogen peroxide into a fuel rich gas; and (d) passing the fuel rich gas through a turbine (20′), thereby using high concentrations of hydrogen peroxide to drive the turbine. Thus, by utiliizing a fuel rich pre-burner (50) that operates at a very low mixture ratio, the drive gas for a turbine (20′) can be maintained at moderate temperature levels.

Abstract: An apparatus is provided for burning a fuel and nitrous oxide. The apparatus has a combustor, a catalyst, a nitrous oxide supply passage for directing the nitrous oxide to a contact position with the catalyst, and a fuel supply passage for supplying the fuel to the combustor. The catalyst is for facilitating decomposition of the nitrous oxide, and the combustor is for burning the fuel, the decomposed nitrous oxide and/or further nitrous oxide decomposed in the reaction.

Abstract: 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.

Abstract: A process for the production of a transverse thrust in a flying object in which a defined quantity of a monergol propellent substance is introduced into a propulsion unit, which is arranged transversely relative to a longitudinal axis of the flying object to produce a thrust transverse to the longitudinal axis of the flying object. The propulsion unit has a combustion chamber, a supersonic nozzle connected to the combustion chamber and a source of heat to combust the propellant substance and produce the desired thrust for a prescribed time.

Abstract: 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.

Abstract: 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 firther 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.

Abstract: 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.

Abstract: A monopropellant assisted solid rocket engine of the present invention is comprised of a combination of a solid rocket engine with nitromethane monopropellant injected into the rocket motor. By controlling the rate at which the monopropellant is injected the thrust of the rocket engine can be controlled.

Abstract: A method, device and composition for achieving ignition and sustained combustion using a solid consumable catalytic bed (CCB) is described. The CCB accomplishes this by decomposition of an injected fluid. Initially this reaction is catalytic or hypergolic in nature, eventually becoming entirely thermal as the CCB is consumed in the reaction generated. The CCB may be placed in a hybrid motor system such that the decomposed injected fluid will undergo combustion with the solid grain. When the injected fluid is high concentration hydrogen peroxide the catalytic materials of construction for the CCB are selected from the metallic hydride family, the manganese oxide family and the cuprocyanide family.

Abstract: A method for decomposing hydrogen peroxide which comprises contacting the hydrogen peroxide with a catalyst having a surface consisting of a mixture of ruthenium with at least one metal of the group consisting of iridium and platinum in which the ruthenium is about 20 to about 70 atom percent of said metals.

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: A supersonic combustion air breathing jet engine and method of igniting fuel. The engine has means for providing a spatially controlled combustion distribution of fuel with an ignitor that provides a volumetrically diffuse discharge of energy to initiate a controlled relatively rapid combustion of fuel in a combustion zone such that combustion distribution in relatively high speed gas flows through the combustion zone can be initiated and controlled without dependence upon a flame holder or relatively high local static gas temperature in the combustion zone.

Abstract: An improved method of operating a scramjet engine for powering an aircraft at supersonic velocity is disclosed. The method includes the steps of providing supersonic compressed airflow in a combustor, supplying fuel to the compressed airflow in the combustor, and providing a monopropellant adjacent to the airflow and the fuel. The monopropellant is effective for expanding in the combustor for mixing the airflow and the fuel for combustion of the airflow and fuel for generating combustion gases. In a preferred embodiment of the invention, the monopropellant is hydrazine and is effective for obtaining a specific volumetric increase of about 20,000:1. An apparatus for carrying out the method of the invention is also disclosed.

Abstract: The method consists, by briefly and periodically interrupting feeding of fuel with the aid of the electrovalve (1), of creating sudden pressure oscillations in the injection chamber (3), these oscillations expelling the impurities in a pasty or possible solid state towards the nozzle (6).Application for space ships.

Abstract: Electronically excited nitrogen fluoride, NF*, is generated by dissociating fluoride azide, FN.sub.3. In a preferred embodiment, the FN.sub.3 is reacted with vibrationally excited molecules such as hydrogen halide, deuterium halide, carbon dioxide, or nitrogen. In second and third embodiments, the FN.sub.3 is dissociated by laser pumping or by detonation. The NF* can provide a short wavelength laser by pumping the NF(b-X) transition in a resonant chamber or by the addition of an emitting species such as BiF to convert the stored energy of the NF* to photons from the emitting species.

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: Disclosed is a single control thruster having the expanded capability of operating at various thrust levels and more than one propellant fluid so that the number of control thrusters for a maneuvering vehicle can be reduced to one third from that now required for appropriate maneuverability in space, resulting in large cost savings and improved reliability. Also disclosed is a "plug in" package with control thruster which can be removed from the vehicle and replaced to make the vehicle easily maintainable.

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 gas generator for passing pressurized liquid monopropellants therethrough or causing exothermic decomposition of the monopropellants. A porous catalytic metal plate is used as the degeneration bed. The monopropellant decomposes exothermically upon contact with the catalytic plate. The porosity is obtained by making the plate from an alloy of the catalyst metal and one other metal, the other metal is then etched away by an acid that does not attack the catalyst metal. The porosity is controlled by the amount of other metal used. Surface areas of several hundred times the original plate surface area are obtainable. The mechanical characteristics of the metal plate allow for greater design flexibility than was available with decomposition beds made of refractory material.

Abstract: Hydrazine thruster 10 is mounted on support flange 14 with thermal mass 12 therebetween. The thermal mass 12 extracts sufficient heat so that the incoming hydrazine in inlet line 20, as well as that portion of the decomposition catalyst contained within the inlet portion of chamber housing 24, is maintained at a temperature below the hydrazine saturation temperature at the pressure within chamber housing 24 so that at any on/off operating duty cycles for that installation, the hydrazine is discharged into the catalyst in chamber housing 24 as liquid.

Abstract: Hydrazine thruster 30 minimizes impulse bit degradation by making the hydrazine more reactive with the catalyst 66 by using higher temperature hydrazine and smaller catalyst grain, and also concentrates the injected hydrazine in smaller catalyst volume 66 so that heat released aids decomposition of a greater quantity of injected hydrazine.