Goods & Services

Chemical additives for use in the production of fuels; industrial chemicals. Fuel; fuel mixtures. Thrusters for air and space vehicle engines; rocket propulsion engines. Rockets; propelling pyrotechnic mixtures for rocket engines (term considered too vague by the International Bureau pursuant to Rule 13 (2) (b) of the Regulations). Satellite fuelling. Science and technology services; research services; design services; technical research; development of engines; development of air and space vehicles.

Goods & Services

Chemical additives for use in the production of fuels; industrial chemicals. Fuel; fuel mixtures. Thrusters for air and space vehicle engines; rocket propulsion engines. Rockets; propelling pyrotechnic mixtures for rocket engines (term considered too vague by the International Bureau pursuant to Rule 13 (2) (b) of the Regulations). Satellite fuelling. Science and technology services; research services; design services; technical research; development of engines; development of air and space vehicles.

Goods & Services

Fuel; fuel mixtures.

Goods & Services

Fuel; fuel mixtures

Goods & Services

Fuel; fuel mixtures. Thrusters for air and space vehicle engines; rocket propulsion engines.

Goods & Services

Fuel; fuel mixtures Thrusters for air and space vehicle engines; rocket propulsion engines

Goods & Services

Fuel; fuel mixtures. Thrusters for air and space vehicle engines; rocket propulsion engines.

Goods & Services

Fuel; Fuel mixtures.

Goods & Services

Chemical additives for use in the production of fuels; industrial chemicals. Fuel; fuel mixtures. Thrusters for air and space vehicle engines; rocket propulsion engines. Rockets; propelling pyrotechnic mixtures for rocket engines. Satellite fuelling. Science and technology services; research services; design services; technical research; development of engines; development of air and space vehicles.

Goods & Services

Chemical additives for use in the production of fuels; industrial chemicals. Fuel; fuel mixtures. Thrusters for air and space vehicle engines; rocket propulsion engines. Rockets; propelling pyrotechnic mixtures for rocket engines. Satellite fuelling. Science and technology services; research services; design services; technical research; development of engines; development of air and space vehicles.

Abstract

The present invention relates to an electrical heater assembly (1) for liquid propellant chemical rocket engines, and more particularly to such heater assembly comprising a heating cable (30) and a heater support (10), wherein the heater support exhibits a groove (17) in which the cable is accommodated, and wherein the heating cable is attached to the support by means of brazing (40) and/or by means of an enclosing member, as well as a liquid propellant chemical rocket engine provided with the heater assembly.

IPC Classes  ?

• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
• F02K 9/68 - Decomposition chambers
• B23K 1/00 - Soldering, e.g. brazing, or unsoldering

Abstract

The present invention relates to an ignition system for a liquid propellant chemical rocket engine, which comprises a thermal-catalytic element (20) for initiating decomposition of the liquid propellant, and an electrical heater (30) for electrically preheating the thermal-catalytic element, wherein the thermal-catalytic element is thermally connected to the electrical heater, both of which are located in a flow path of the propellant, a rocket engine, and a preburner, respectively, comprising the ignition system, as well as a method of preheating a liquid propellant rocket engine using the system, and a spacecraft comprising such engine.

IPC Classes  ?

• F02K 9/52 - Injectors
• F02K 9/68 - Decomposition chambers

Abstract

The present invention relates to a liquid propellant chemical rocket engine reactor Thermal Management System (TMS), which system comprises a reactor comprising a thermally conductive reactor housing, a heat bed, and a catalyst bed, which system further comprises an injector configured to spray the propellant in the form of a cone towards a portion of the circumference of the inner surface of the reactor housing, and an electrical heater located on the outside or inside of the reactor housing for heating said portion of the inner surface of the reactor housing. The invention also relates to a rocket engine comprising the reactor Thermal Management System, a spacecraft comprising the engine, as well as to a method of decomposing a liquid propellant, which can be carried out using the inventive reactor Thermal Management System, wherein vaporization of the propellant is accomplished by bringing the propellant into close proximity to, or to imping on, a portion of the circumference of said inner reactor surface adjacent to the injector.

IPC Classes  ?

• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
• F23R 3/30 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
• F23R 3/40 - Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
• F23R 7/00 - Intermittent or explosive combustion chambers
• F02K 9/52 - Injectors
• F02K 9/68 - Decomposition chambers

Abstract

The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit maneuvers 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 a low-hazard liquid oxidizer-rich monopropellant, respectively.

IPC Classes  ?

• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
• C06B 47/00 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
• C06B 47/02 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
• C06D 5/08 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
• C06B 31/00 - Compositions containing an inorganic nitrogen-oxygen salt
• F02K 9/52 - Injectors
• F02K 9/56 - Control
• F02K 9/60 - Constructional partsDetails not otherwise provided for

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.

IPC Classes  ?

• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
• F23R 3/40 - Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
• F23R 3/30 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
• C06B 31/28 - Compositions containing an inorganic nitrogen-oxygen salt the salt being ammonium nitrate
• B01J 37/02 - Impregnation, coating or precipitation
• B01J 23/38 - Catalysts comprising metals or metal oxides or hydroxides, not provided for in group of noble metals

Abstract

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 liquidpropellants 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.

IPC Classes  ?

• C06B 47/00 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
• C06B 47/02 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
• C06D 5/08 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants

Abstract

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) orbitraising, 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.

IPC Classes  ?

• C06B 47/00 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
• C06B 47/02 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
• C06D 5/08 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants

Abstract

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 a low-hazard liquid oxidizer-rich monopropellant, respectively.

IPC Classes  ?

• C06B 47/00 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
• C06B 47/02 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
• C06D 5/08 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants

Abstract

Reactor for the decomposition of ammonium dinitramide-based liquid monopropellants into hot combustible gases for combustion in a combustion chamber (50), and rocket engine or thruster comprising such reactor, which reactor comprises an inner reactor housing (45) accommodating a heat bed (25) and a catalyst bed (30), and separating the heat bed and catalyst bed from contact with the inner surface of the reactor housing (5).

IPC Classes  ?

• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants

Abstract

Reactor for the decomposition of ammonium dinitramide-based liquid monopropellants into hot combustible gases for combustion in a combustion chamber (50), and rocket engine or thruster comprising such reactor, wherein the reactor comprises a heat bed (25) and a catalyst bed (30), the heat bed exhibiting catalytic activity.

IPC Classes  ?

• F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants

Abstract

The present invention generally relates to a method of converting chemical energy from aqueous,liquid, ADN-based monopropellantsinto mechanical energy and a corresponding arrangement comprising a reactor for combustion of aqueous,liquid,ADN-based monopropellants and a mechanical-energy converting device, and to a vehicle, vessel, missile, secondary power plant, EPU, APU and the like comprising such arrangement.

IPC Classes  ?

• F23L 7/00 - Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
• F23R 7/00 - Intermittent or explosive combustion chambers

Abstract

Ammonium dinitramide based liquid monopropellants containing ADN, water, ammonia and, optionally, methanol, exhibiting improved low-temperature operational range are disclosed.

IPC Classes  ?

• C06D 5/08 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
• C06B 31/00 - Compositions containing an inorganic nitrogen-oxygen salt