Space propulsion system

A space propulsion system (1) in combination with a satellite having a weight of less than 100 kg,

• the space propulsion system (1), comprising:
• an electrolytic system (2), fed by an electric source (6), for division of water into oxygen and hydrogen while in satellite orbit;
• a combustion chamber (10) comprised of a cylindrical container (11) having cylindrical walls (13) extending from a first end (12) to an opposite second end (14),
• the first end (12) being provided with:
• i) a first injection duct (15) arranged at a tangent to the cylindrical walls (13), the first injection duct (15) for injection of oxygen from the electrolytic system (2), the oxygen being injected in a direction tangential to said cylindrical walls so as to induce a helical combustion path in the combustion chamber (10), wherein the first injection duct (15) is configured to provide a first flow range, expressed as mass per time unit, and
• ii) a second injection duct (16) provided perpendicular to the cylindrical walls (13) of the combustion chamber (10), wherein the second injection duct (16) is configured to provide a second flow range, wherein the second injection duct (16) is parallel to the plane of the first end (12), a position of the second injection duct (16) being such that an inlet in the combustion chamber (10) takes place at the inlet of the first injection duct (15), so that a gaseous flow injected through the first injection duct (15) intersects another gaseous flow injected through the second injection duct (16), the second injection duct (16) for injection of hydrogen from the electrolytic system (2), the hydrogen being injected in a direction perpendicular to said cylindrical walls,
• wherein the first flow rate is larger than the second flow rate, the oxygen from the electrolytic system (2) requiring the larger, first flow range, expressed as mass per time unit, is injected into the combustion chamber (10) using the first injection duct (15) that is arranged at a tangent to the cylindrical walls (13) of the combustion chamber (10), and the hydrogen from the electrolytic system (2) requiring the smaller, second flow range is injected through the second injection duct (16) that is provided perpendicular to the cylindrical walls (13) of the combustion chamber (10);
• a discharge duct (19) connected, at another tangent, to the cylindrical walls (13) at the opposite end (14), the discharge duct (19) arranged in a direction tangential to said cylindrical walls (13) so as to receive and direct said helical combustion path;
• and
• a supersonic nozzle (20), connected to said discharge duct (19) for discharging the combustion products in the combustion chamber,
• the space propulsion system (1) being configured for providing propulsion of the satellite,
• wherein the electrolytic system (2) is arranged and configured for injection of the oxygen and the hydrogen in the first injection duct and in the second injection duct, respectively and wherein the electrolytical system divides the water into the oxygen and the hydrogen in optimum stoichiometric proportions which provides performance with consequent production of only water vapour outgoing from the combustion chamber (10).

A space propulsion system (1), comprising:

• an electrolytic system (2), fed by an electric source (6), for division of water into oxygen and hydrogen;
• and
• a combustion chamber (10) including a cylindrical container (11) having cylindrical walls (13) comprising a first end (12) provided at least with a first injection duct (15) for a combustion agent, for the injection according to a direction tangential to said cylindrical walls so as to induce a helical combustion path in the combustion chamber (10), the first injection duct (15) for injection of the oxygen serving as the combustion agent, a second injection duct (16) for hydrogen serving as a fuel in direction perpendicular to said cylindrical walls, and an opposite end (14) provided with a discharge duct (19) arranged according to a direction tangential to said cylindrical walls (13) so as to receive and direct said helical path;
• and
• a supersonic nozzle (20), connected to said discharge duct (19) for discharging the combustion products in the combustion chamber, the combustion agent requiring a larger flow range, expressed as a mass per time unit, being injected into the combustion chamber (10) using the tangential, first injection duct (15), and the fuel requiring a smaller flow range being injected through the perpendicular, second injection duct (16),
• wherein the electrolytic system (2) is arranged and configured for injection of the oxygen in the first injection duct and injection of the hydrogen in the second injection duct, respectively, and
• wherein the electrolytical system divides the water into the oxygen and the hydrogen in optimum stoichiometric proportions which provides performance with consequent production of only water vapour outgoing from the combustion chamber (10).