Through this work we show the development of small hybrid rocket thrusters intended for attitude control systems of small satellites and space-crafts. These thrusters have the advantage of being controllable and having higher specific impulse than the traditional solid fuel thrusters or hydrazine based thrusters. An internal ballistic model of the small hybrid thrusters is shown together with numerical results for the thrust-curves and other relevant parameters. The internal ballistic model is shown to be influenced by the regression speed and the need for higher regression speed fuel-oxidizer pairs is, hence, shown. In the present study we also show how to couple the hybrid combustion process with the unsteady flow. Moderately high specific impulses can be obtained by using polypropylene as fuel and NO2 as oxidizer. Detailed discussion is done on the construction of the thrusters as well as the engineering solutions for the combustion chamber, injector and nozzle. Several experimental thrust-curves are shown together with the estimation of total impulse and specific impulse.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Small hybrid thruster development for small satellite attitude control system


    Beteiligte:


    Erscheinungsdatum :

    01.06.2013


    Format / Umfang :

    629022 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Cold Gas Thruster and Controller Development for Satellite Attitude Control

    Sedaki, Huda / Koyuncu, Emre / Karabeyoglu, Mustafa A. et al. | AIAA | 2024


    Attitude Control System for Small Satellite

    Hosokawa, S. / Masumoto, Y. / Takezawa, S. et al. | British Library Online Contents | 2006


    Rate damping control for small satellite using thruster

    Weidong, Huang | Online Contents | 2004


    Thruster support for small satellite installation

    CHEN PENGFEI | Europäisches Patentamt | 2022

    Freier Zugriff

    Skylab thruster attitude control system

    Wilmer, G. E., Jr. | NTRS | 1974