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.

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.

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.

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: 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.

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 hydrogen peroxide, respectively.

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) 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.

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, which reactor further comprises an inner reactor housing accommodating a heat bed and a catalyst bed, and separating the heat bed and catalyst bed from contact with the inner surface of the reactor housing.

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: 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: Preparation of sintering resistant hexaaluminates, AAl11O18, wherein A is an alka-line earth or rare earth metal, and more particularly lanthanum, by a combination of sol-gel and microemulsion techniques using a water soluble salt of A, and a method of forming spherical pellets thereof are disclosed.

Abstract: A method of preparing spherical pellets from a slurry comprising a ceramic powder, a solvent, and any desired additives, by means of a drop-generating orifice to which said slurry is fed is described, wherein the drops are released from said orifice by means of a relative flow of a liquid medium which is a poor solvent for the solvent of the slurry, formed into spherical bodies in said liquid medium by means of the action of surface tension, and thereafter treated for consolidation. More specifically, the present invention relates to the preparation of pellets of a catalyst or catalyst support material, suitable for use in high temperature conditions.

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 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.

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 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.

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 method of preparing spherical pellets from a slurry comprising a ceramic powder, a solvent, and any desired additives, by means of a drop-generating orifice to which said slurry is fed is described, wherein the drops are released from said orifice by means of a relative flow of a liquid medium which is a poor solvent for the solvent of the slurry, formed into spherical bodies in said liquid medium by means of the action of surface tension, and thereafter treated for consolidation. More specifically, the present invention relates to the preparation of pellets of a catalyst or catalyst support material, suitable for use in high temperature conditions.

Abstract: Preparation of sintering resistant hexaaluminates, AAl11O18, wherein A is an alka-line earth or rare earth metal, and more particularly lanthanum, by a combination of sol-gel and microemulsion techniques using a water soluble salt of A, and a method of forming spherical pellets thereof are disclosed.

Abstract: Liquid propellants for the purpose of generating hot gases are described, which propellants comprise solution of a dinitramide compound and a fuel, and are especially suited for space applications, and exhibit the following properties exhibit the following properties: low toxicity; no toxic or combustible vapors; high theoretical specific impulse (as compared to hydrazine); high density (as compared to hydrazine); easily ignitable; storable at a temperature between +10° C. and +50° C.; low sensitivity.