Patent ID: 11897636
Assignee: ARIANEGROUP GMBH
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC B  F  H  Y | IPC B  F  H

Claim 0:
1. A rocket propulsion system comprising
a first cryogenic tank for a first propellant,
a second cryogenic tank for a second propellant,
at least one repeatedly ignitable main propulsion unit configured to be fed, in a propulsion phase of the rocket propulsion system, by the first and the second cryogenic tank,
a first auxiliary propulsion unit operable in a ballistic phase by means of a first gas pressure accumulator, and
at least one further auxiliary propulsion unit operable in a ballistic phase by means of a second gas pressure accumulator,
wherein the rocket propulsion system is assigned an energy conversion unit, which is configured at least to charge the first and the second gas pressure accumulator,
wherein the energy conversion unit has at least one fuel cell configured to generate electrical energy,
the fuel cell having a first reception chamber for the first propellant, and a second reception chamber for the second propellant,
wherein a first evaporation line is provided in a region of an upper surface of the first cryogenic tank and configured to feed the first propellant in a gaseous phase to the first reception chamber,
and a second evaporation line is provided in a region of an upper surface of the second cryogenic tank and configured to supply the second propellant in a gaseous phase to the second reception chamber.