The present disclosure relates to systems, devices, and methods for spacecraft propulsion. In an embodiment, the present disclosure relates to an apparatus comprising a heat exchanger body defining a plurality of propellant channels configured to contain a propellant, a central cavity configured to contain a working fluid and fluidically connected to a plurality of working fluid channels that extend along a radial dimension of the apparatus, and a nozzle fluidically connected to the plurality of propellant channels and configured to expel the propellant.
SYSTEMS, DEVICES, AND METHODS FOR SPACECRAFT PROPULSION WITH A HEAT EXCHANGER
2025-01-23
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS |
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