Abstract: A spacecraft is equipped with a low and high thrust space propulsion system including at least one water reservoir (1) containing liquid water, a high thrust propulsion part and a low thrust propulsion part. The high thrust propulsion part has a high thruster including a regulation valve (V1) for drawing water from the liquid water reservoir (1), a device for splitting (2) liquid water into gaseous hydrogen and gaseous oxygen, relative storage tanks (3, 4), a combustion chamber (5) in which the gaseous hydrogen reacts with the gaseous oxygen and an exhaust nozzle (6) from the combustion chamber (5). The low thrust propulsion part comprises a liquid water supply line (10) and a plurality of liquid water outlets in a plurality of branches (11-1n) individually including a regulating valve (21-2n), a vaporization chamber (31-3n) and an expansion nozzle (41-4n).

Abstract: A spacecraft is equipped with a low and high thrust space propulsion system including at least one water reservoir (1) containing liquid water, a high thrust propulsion part and a low thrust propulsion part. The high thrust propulsion part has a high thruster including a regulation valve (V1) for drawing water from the liquid water reservoir (1), a device for splitting (2) liquid water into gaseous hydrogen and gaseous oxygen, relative storage tanks (3, 4), a combustion chamber (5) in which the gaseous hydrogen reacts with the gaseous oxygen and an exhaust nozzle (6) from the combustion chamber (5). The low thrust propulsion part comprises a liquid water supply line (10) and a plurality of liquid water outlets in a plurality of branches (11-1n) individually including a regulating valve (21-2n), a vaporization chamber (31-3n) and an expansion nozzle (41-4n).

Abstract: A micro-combustion device generating electrical power raises global performance of the system, is compact, and reduces losses by utilizing an induced helical path. The device includes: injection ducts inserting a combustion agent, a fuel and/or a mixture thereof wherein the injection of the combustion agent takes place tangentially to the internal cylindrical wall, inducing a helical combustion path, the internal cylindrical walls of the chamber having a deposition of catalytic material to accelerate the combustion reaction; a turbo compressor group, including a compressor, feeding under pressure the combustion chamber through the injection ducts, and a turbine, receiving the flue gases from the discharge duct, compressor and turbine being keyed on the same axis, whereon a generator of electrical power, in turn, is keyed; and a fuel cell, fed by the flue gases through the turbine and by an oxidizing agent, implementing an electrochemical process generating additional electrical power.

Abstract: A space propulsion system can serve miniaturised satellites, but can be scaled easily, and includes: a combustion chamber implemented by a cylindrical container having cylindrical walls, a first end provided with at least an injection duct for a combustion agent, a fuel and/or a mixture thereof, for the injection according to a direction tangential to the cylindrical walls so as to induce a helical combustion path in the combustion chamber, a possible additional perpendicular injection duct for a fuel or a combustion agent, and an opposite end provided with a discharge duct arranged according to a direction tangential to the cylindrical walls so as to receive and direct the helical path, wherein the cylindrical walls in case have a deposition of catalytic material inside thereof, for accelerating the combustion reaction; and a supersonic nozzle, connected to the discharge duct for discharging the combustion products in the combustion chamber.

Abstract: A micro-combustion device generating electrical power raises global performance of the system, is compact, and reduces losses by utilizing an induced helical path. The device includes: injection ducts inserting a combustion agent, a fuel and/or a mixture thereof wherein the injection of the combustion agent takes place tangentially to the internal cylindrical wall, inducing a helical combustion path, the internal cylindrical walls of the chamber having a deposition of catalytic material to accelerate the combustion reaction; a turbo compressor group, including a compressor, feeding under pressure the combustion chamber through the injection ducts, and a turbine, receiving the flue gases from the discharge duct, compressor and turbine being keyed on the same axis, whereon a generator of electrical power, in turn, is keyed; and a fuel cell, fed by the flue gases through the turbine and by an oxidizing agent, implementing an electrochemical process generating additional electrical power.