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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    Titel :

    Thrust vector control for hybrid propellants rocket engine with embedded fluid injection ports


    Beteiligte:

    Erscheinungsdatum :

    29.10.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS



    THRUST VECTOR CONTROL FOR HYBRID PROPELLANTS ROCKET ENGINE WITH EMBEDDED FLUID INJECTION PORTS

    ELZEIN BACHAR / GAGNON MIGUEL / GOULET-BOURDON MAXIME | Europäisches Patentamt | 2025

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    Preliminary Design of a Hybrid Rocket Liquid Injection Thrust Vector Control System

    Case, E.G. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2008