This paper develop a calculus model based on dedicated experiment for an innovative Reaction Control System (RCS) using hybrid rocket engine technology. Our RCS uses several hybrid micro-thrusters with their thrust modulated by a separate control system. For RCS, each of the thrusters is able to burn a few minutes and its thrust is modulated within certain limits by controlling the oxidizer flow. These studies were presented in RAST 2013 and are based on our own experiments performed in Electromecanica Ploiesti. Based on this concept we achieve a calculation of the performances of the RCS and make a comparison between theoretical and experimental results. Conclusions and discussions will be focused on technological possibilities to improve RCS performance and possible areas of application of it.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Reaction control system using hybrid micro-thrusters, theoretical and experimental results


    Beteiligte:


    Erscheinungsdatum :

    01.06.2015


    Format / Umfang :

    447623 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Reaction Control System using hybrid micro-thrusters for guided sounding rocket

    Chelaru, Teodor Viorel / Chelaru, Adrian | IEEE | 2013


    Flight control using distributed micro-thrusters

    SANCHEZ JASON D / GARBUZ PIOTR A / ZONENBERG ANDREW D | Europäisches Patentamt | 2016

    Freier Zugriff

    Theoretical and experimental evaluation of pulsed plasma thrusters

    ANDRENUCCI, M. / LAZZARETTI, R. | AIAA | 1976


    Cold Gas Micro Thrusters

    Eriksson, Anders / Stenmark, Lars | AIAA | 2002