THRUST VECTOR CONTROL FOR HYBRID PROPELLANTS ROCKET ENGINE WITH EMBEDDED FLUID INJECTION PORTS
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United States of America
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Issued Date -
Jan 9, 2025
app pub date -
Sep 25, 2024
filing date -
Sep 25, 2024
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Abstract
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.
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