The present invention concerns itself with a nominal 5 lbF thrust attitude control engine which derives its thrust from the non-catalytic decomposition of hydrazine. In essence, the thruster of this invention is composed of an elongated cylindrical, pressure chamber having an elongated cylindrical heating well positioned within the center of the chamber along its longitudinal axis. An electrical heater is positioned within the well. The chamber is operationally connected to a source of hydrazine which enters the chamber through an injection tube positioned tangential to the interior surface of the chamber. The configuration and position of the injector tube as well as the heating means are critical components of the thruster of this invention. These essential elements, with their unique placement and configuration, are responsible for providing the long life, high thrust and the means for maintaining the thruster at the temperature level necessary for successful pulsed as well as steady state operation. Accordingly, the primary object of this invention is to provide a monopropellant hydrazine thruster capable of operating at a 5 lbF nominal thrust level with a 3 to 1 blow-down range.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Non-Catalytic Hydrazine Thruster


    Beteiligte:
    W. S. Davis (Autor:in)

    Erscheinungsdatum :

    1981


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Electrothermal hydrazine thruster development

    MURCH, C. / HUNTER, C. | AIAA | 1972



    Hydrazine electrothermally augmented thruster /HEAT/

    FINSTON, R. / MEESE, R. | AIAA | 1979


    Augmented electrothermal hydrazine thruster development

    SCHMITZ, H. D. / STEENBORG, M. | AIAA | 1983