A rocket propulsion system comprising a first cryogenic tank and a second cryogenic tank, wherein the first cryogenic tank is filled with a first propellant, and the second cryogenic tank is filled with a second propellant, for purposes of feeding at least one repeatedly ignitable main propulsion unit in a propulsion phase of the rocket propulsion system. For purposes of tank pressurization via at least a low level of acceleration in a ballistic phase, a first auxiliary propulsion unit can be operated by means of a first gas pressure accumulator, and at least one further auxiliary propulsion unit can be operated by means of a further gas pressure accumulator, and the rocket propulsion system is assigned an energy conversion unit, which is designed at least to charge the first and the second gas pressure accumulator, preferably in the ballistic phase.
Rocket propulsion system, method, and spacecraft
2024-02-13
Patent
Elektronische Ressource
Englisch
IPC: | B64G Raumfahrt , COSMONAUTICS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F17C Behälter zum Aufnehmen oder Speichern verdichteter, verflüssigter oder verfestigter Gase , VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES / H01M Verfahren oder Mittel, z.B. Batterien, für die direkte Umwandlung von chemischer in elektrische Energie , PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY |