A rocket engine has: a combustion chamber having a chamber inlet for receiving an oxidizer and a chamber outlet for expelling combustion gases in an environment outside the combustion chamber; a manifold having a manifold inlet fluidly connectable to a source of the oxidizer and a manifold outlet; a catalyst having a catalyst inlet fluidly connected to the manifold outlet and a catalyst outlet; and an injector plate having a injector inlet fluidly connected to the catalyst outlet and an injector outlet fluidly connected to the chamber inlet.
Rocket engine with integrated oxidizer catalyst in manifold and injector assembly
13.08.2024
Patent
Elektronische Ressource
Englisch
Variable-flow hybrid rocket oxidizer injector
AIAA | 2001
|Oxidizer-Rich Preburner for Advanced Rocket Engine Application
British Library Conference Proceedings | 1994
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