Systems and methods for design, manufacture, and test of space thruster propulsion systems

A method of manufacturing a rocket, the method comprising:

• additively manufacturing a combustion chamber;
• additively manufacturing an injector that is integrally coupled with the combustion chamber;
• and
• additively manufacturing propellant management structures that are integrally coupled with the injector and the combustion chamber that include additively manufacturing a regenerative jacket around the combustion chamber that includes:
• additively manufacturing a plurality of ribs that couple with a hot wall of the combustion chamber and a cold wall of the combustion chamber and are oriented to set a propellant flow to impinge upon a plurality of fins;
• and
• additively manufacturing the plurality of fins that extend from the hot wall of the combustion chamber towards the cold wall of the combustion chamber and protrude into one or more flow paths between the plurality of ribs, wherein the plurality of ribs and the plurality of fins form a plurality of stages that include:
• a first stage from the plurality of stages that includes a first plurality of ribs from the plurality of ribs and a first plurality of fins from the plurality of fins;
• and
• a second stage from the plurality of stages that includes a second plurality of ribs from the plurality of ribs and a second plurality of fins from the plurality of fins, wherein the second stage follows discontinuously from the first stage in the one or more flow paths between the plurality of ribs.