Systems, devices, and methods for spacecraft propulsion with a heat exchanger
AssigneePortal Space Systems Inc.
InventorsJeffery T. Thornburg, Prashaanth Ravindran
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Abstract
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.
Claims14
An apparatus comprising:
- a heat exchanger body defining a plurality of propellant channels configured to contain a propellant and extending along an axial dimension of the apparatus;
- the heat exchanger body defining a central cavity configured to contain a working fluid and extending along the axial dimension of the apparatus, the central cavity 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.
An apparatus, comprising:
- a heat exchanger body defining a plurality of propellant feed channels and a plurality of working fluid channels, the heat exchanger body configured to transfer heat from working fluid recirculating through the working fluid channels to the propellent;
- and
- a nozzle fluidically connected to the plurality of propellant feed channels and configured to expel the propellant after being heated by the working fluid via the heat exchanger body to produce thrust without the propellant being combusted.
Dependencies are inferred from the claim text.