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US 11,143,144 B2Granted
Rocket propulsion system and method for operating a rocket propulsion system
AssigneeArianegroup SAS
InventorsUlrich Gotzig, Malte Wurdak
Life of this patent
Estimating the term…
Abstract
A rocket propulsion system comprises a combustion chamber, a hydrogen-oxygen supply system connected to the combustion chamber, which hydrogen-oxygen supply system is configured to conduct hydrogen and oxygen into the combustion chamber, and a coolant supply system connected to the combustion chamber, which coolant supply system is configured to conduct a combustible coolant into the combustion chamber. An ignition system of the rocket propulsion system is configured to initiate combustion of the hydrogen-oxygen-coolant mixture in the combustion chamber.
Claims12
A rocket propulsion system comprising:
- a combustion chamber of the rocket propulsion system connected to a thruster with an exit opening for generating thrust;
- a hydrogen-oxygen supply system connected to the combustion chamber, which hydrogen-oxygen supply system is configured to conduct hydrogen and oxygen into the combustion chamber;
- a coolant supply system connected to the combustion chamber, which coolant supply system is configured to supply a combustible coolant to the combustion chamber;
- and
- an ignition system configured to initiate combustion of the hydrogen-oxygen-coolant mixture in the combustion chamber;
- wherein the ignition system comprises a catalyst chamber arranged in the combustion chamber, a hydrogen supply duct, and an oxygen supply duct;
- wherein the combustion chamber is provided with an overall combustion section located downstream of an exit area of the catalyst chamber, wherein the overall combustion section is configured to be supplied at the same time with gases exiting the catalyst chamber, with oxygen directly supplied by the oxygen supply duct of the ignition system to the overall combustion section, and with coolant supplied to the combustion chamber via the coolant supply system;
- and
- wherein the coolant supply system comprises a coolant duct and wherein the hydrogen supply duct is disposed between the oxygen supply duct and the coolant duct.
6 more elements
A rocket propulsion system comprising:
- a combustion chamber of the rocket propulsion system connected to a thruster with an exit opening for generating thrust;
- a hydrogen-oxygen supply system connected to the combustion chamber, which hydrogen-oxygen supply system is configured to conduct hydrogen and oxygen into the combustion chamber;
- a coolant supply system connected to the combustion chamber, which coolant supply system is configured to supply a combustible coolant to the combustion chamber;
- and
- an ignition system configured to initiate combustion of the hydrogen-oxygen-coolant mixture in the combustion chamber;
- wherein the ignition system comprises a catalyst chamber arranged in the combustion chamber, a hydrogen supply duct, and an oxygen supply duct;
- and
- wherein the combustion chamber is provided with an overall combustion section located downstream of an exit area of the catalyst chamber, wherein the overall combustion section is configured to be supplied at the same time with gases exiting the catalyst chamber, with oxygen directly supplied by the oxygen supply duct of the ignition system to the overall combustion section, and with coolant supplied to the combustion chamber via the coolant supply system;
- and
- wherein the catalyst chamber has an annular cross section, through which the oxygen supply duct passes.
7 more elements
A method for operating a rocket propulsion system, comprising:
- connecting a combustion chamber of the rocket propulsions system to a thruster with an exit opening for generating thrust;
- conducting of hydrogen and oxygen into the combustion chamber;
- conducting of a combustible coolant into the combustion chamber;
- and
- initiating combustion of the hydrogen-oxygen-coolant mixture in the combustion chamber;
- wherein the ignition system comprises a catalyst chamber arranged in the combustion chamber, a hydrogen supply duct, and an oxygen supply duct;
- wherein the combustion chamber is provided with an overall combustion section located downstream of an exit area of the catalyst chamber, wherein the overall combustion section is supplied, at the same time, with gases exiting the catalyst chamber, with oxygen directly supplied by the oxygen supply duct of the ignition system to the overall combustion section, and with coolant supplied to the combustion chamber via the coolant supply system;
- and
- wherein the coolant supply system comprises a coolant duct and wherein the hydrogen supply duct is disposed between the oxygen supply duct and the coolant duct.
6 more elements
Dependencies are inferred from the claim text.