Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.
ROCKET PROPULSION SYSTEMS AND ASSOCIATED METHODS
RAKETENTRIEBWERKE UND ZUGEHÖRIGE VERFAHREN
SYSTÈMES DE PROPULSION DE FUSÉES ET PROCÉDÉS ASSOCIÉS
2022-10-26
Patent
Electronic Resource
English