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
29.10.2024
Patent
Elektronische Ressource
Englisch
THRUST VECTOR CONTROL FOR HYBRID PROPELLANTS ROCKET ENGINE WITH EMBEDDED FLUID INJECTION PORTS
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