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.
Claims17
-5. (canceled)
A heat exchanger constructed via an additive manufacturing process, comprising:
- depositing a first transverse layer of a refractory metal,
- the refractory metal of the first transverse layer radially surrounding and forming a portion of a wall of a central cavity that is configured to contain a working fluid,
- the refractory metal of the first transverse layer forming portions of walls that define a radial channel, the walls of the radial channel forming an inlet to the radial channel on the wall of the central cavity and an outlet on an exterior radial surface of the heat exchanger, the radial channel configured to route the working fluid from the central cavity to the outlet port;
- and
- depositing a second transverse layer of the refractory metal above the first transverse layer in an axial direction, the refractory metal of the second transverse layer defining a portion of a propellant feed channel that is configured to convey a propellant axially through the heat exchanger such that heat is transferred from the working fluid to the propellant via the refractory metal.
-27. (canceled)
Dependencies are inferred from the claim text.