Rotating detonation engines (RDEs) have been actively researched around the world for application to next-generation aerospace propulsion systems because detonation combustion has theoretically higher thermal efficiency than conventional combustion. Moreover, because cylindrical RDEs have simpler combustors, further miniaturization of conventional combustors is expected. Therefore, in this study, with the aim of applying RDEs to space propulsion systems, a cylindrical RDE with a converging–diverging nozzle was manufactured; the combustor length L c was changed to 0, 10, 30, 50, and 200 mm; and the thrust performance and combustion mode with the different combustor lengths were compared. As a result, four combustion modes were confirmed. Detonation combustion occurred with a combustor length of L c = 0    mm : that is, a converging rotating detonation engine. The thrust performance of this engine was 94 to 100% of the theoretical rocket thrust performance, which is equivalent to the thrust performance of conventional rocket combustion generated at L c = 200    mm . This study shows that detonation combustion can significantly reduce engine weight while maintaining thrust performance.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Thrust Performance of Converging Rotating Detonation Engine Compared with Steady Rocket Engine


    Beteiligte:
    Ishihara, Kazuki (Autor:in) / Yoneyama, Kentaro (Autor:in) / Watanabe, Hiroaki (Autor:in) / Itouyama, Noboru (Autor:in) / Kawasaki, Akira (Autor:in) / Matsuoka, Ken (Autor:in) / Kasahara, Jiro (Autor:in) / Matsuo, Akiko (Autor:in) / Funaki, Ikkoh (Autor:in) / Higashino, Kazuyuki (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2023-02-15


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    IDEAL THERMODYNAMIC PERFORMANCE RESULTS FOR ROTATING DETONATION ROCKET ENGINE THRUST CHAMBERS USING CEA

    Paulson, Eric J. / Kimura, Randon / Hargus, William A. et al. | TIBKAT | 2020


    Ideal Thermodynamic Performance Results for Rotating Detonation Rocket Engine Thrust Chambers Using CEA

    Paulson, Eric J. / Kimura, Randon / Hargus, William A. et al. | AIAA | 2020


    Rocket rotating detonation engine flight demonstrator

    Okninski, Adam / Kindracki, Jan / Wolanski, Piotr | Emerald Group Publishing | 2016



    Thrust Validation of Rotating Detonation Engine System by Moving Rocket Sled Test

    Goto, Keisuke / Kato, Yuichi / Ishihara, Kazuki et al. | AIAA | 2020