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.
RAKETENANTRIEB, VERFAHREN SOWIE RAUMFAHRZEUG
ROCKET ENGINE, METHOD AND SPACECRAFT
MOTEUR DE FUSÉE, PROCÉDÉ, AINSI QU'ENGIN SPATIAL
2024-04-03
Patent
Elektronische Ressource
Deutsch
IPC: | B64G Raumfahrt , COSMONAUTICS |
Europäisches Patentamt | 2021
|Düsenflugzeug und Raketenantrieb
TIBKAT | 1954
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