A hybrid rocket engine system has: an oxidizer tank containing a liquid oxidizer; a rocket engine having a combustion chamber operatively connected to the oxidizer tank; a solid propellant fuel within the combustion chamber; a nozzle fluidly connected to the combustion chamber, the nozzle having a convergent section and a divergent section downstream of the convergent section; and a thrust vector control device operatively connected to the divergent section of the nozzle and operable to inject a fluid through at least one aperture defined through the divergent section for controlling a direction of a thrust generated by the rocket engine.
Thrust vector control for hybrid propellants rocket engine with embedded fluid injection ports
2024-10-29
Patent
Electronic Resource
English
THRUST VECTOR CONTROL FOR HYBRID PROPELLANTS ROCKET ENGINE WITH EMBEDDED FLUID INJECTION PORTS
European Patent Office | 2025
|Rocket Engine Thrust Vector Control Operation Through Secondary Injection
SAE Technical Papers | 1964
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NTRS | 1957
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